Added(A)/Deleted(D) following books

 A  A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER11_2.ipynb
A  A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER12_2.ipynb
A  A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER15_2.ipynb
A  A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER16_2.ipynb
A  A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER17_2.ipynb
A  A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER20_2.ipynb
A  A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER21_2.ipynb
A  A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER3_2.ipynb
A  A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER4_2.ipynb
A  A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER5_2.ipynb
A  A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER7_2.ipynb
A  A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/screenshots/HeatTransfer(3)_2.png
A  A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/screenshots/cycleWorkEff(4)_2.png
A  A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/screenshots/volumetric_Eff(7)_2.png

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+{
+ "cells": [
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "# CHAPTER 11 - Carburetion and Carburettors"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 11.1 PAGE 399"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 2,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Suction at throat = 4447.61 N/m**2 \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "d=0.1#..................#Cylinder bore in m\n",
+    "l=0.12#................#Cylinder stroke in m\n",
+    "N=1800#..................#Engine rpm\n",
+    "d2=0.028#................#Throat diameter in m\n",
+    "Cda=0.8#................#Co efficient of air flow\n",
+    "etaV=0.75#..................#Volumetric efficiency\n",
+    "rhoa=1.2#................#Density of air in kg/m**3\n",
+    "n=4#.......................#No of cylinders\n",
+    "#Calculations\n",
+    "Vs=(pi/4)*d*d*l*n#.................#Stroke Volume in m**3\n",
+    "Va=etaV*Vs#.......................#Actual volume per stroke in m**3\n",
+    "Vas=Va*(N/2)*(1/60)#.............#Actual volume sucked per second\n",
+    "ma=Vas*rhoa#.........................#Air consumed in kg/sec\n",
+    "delp=((ma/(Cda*(pi/4)*d2*d2))**2)/(2*rhoa)#.............#Suction at throat in N/m**2\n",
+    "print \"Suction at throat = %0.2f N/m**2 \"%delp"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 11.2 PAGE 400"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 1,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Suction at the throat = 539.13 N/m**2 \n",
+      "Throat area = 7.72 cm**2 \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt\n",
+    "# Initialisation of Variables\n",
+    "cp=5#.................#Consumption of petrol in kg/h\n",
+    "afr = 16#...............#Air fuel ratio\n",
+    "Af=2*10**(-6)#..............#Fuel orifice area in m**2\n",
+    "z=0.005#................#Distance between tip of jet and level of petrol in float chamber in m\n",
+    "spgrp=0.75#..............#Specific gravity of petrol\n",
+    "rhow=1000#.................#Density of water in kg/m**3\n",
+    "rhoa=1.2#....................#Density of air in kg/m**3\n",
+    "Cda=0.8#...............#Coefficient of discharge for venturi throat\n",
+    "g=9.81#...............#Acceleration due to gravity in m/sec**2\n",
+    "#Calculations\n",
+    "mf=cp/3600#.................#Fuel consumed in kg/sec\n",
+    "delp=(((mf/(Af*Cda))**2)*(1/(2*spgrp*rhow)))+(g*z*spgrp*rhow)#\n",
+    "print \"Suction at the throat = %0.2f N/m**2 \"%delp\n",
+    "ma=mf*afr#................#Air flow rate\n",
+    "Atsqr=((ma/Cda)**2)*(1/(2*rhoa*delp))#....................#Throat area in m**2\n",
+    "print \"Throat area = %0.2f cm**2 \"%(sqrt(Atsqr)*10**4)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 11.3 PAGE 401"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 3,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Diameter of the fuel jet = 1.32 mm\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi,sqrt\n",
+    "# Initialisation of Variables\n",
+    "pc=7.2#.................#Petrol consumed in kg/h\n",
+    "spgrp=0.75#................#Specific gravity of fuel\n",
+    "rhow=1000#.................#Density of water in kg/m**3\n",
+    "t1=300#...................#Temperature of air in Kelvin\n",
+    "afr=15#....................#Air fuel ratio\n",
+    "d2=0.024#....................#Diameter of choke tube in m\n",
+    "z=0.0042#...................#The height of the jet above petrol level in float chamber in m\n",
+    "Cda=0.8#....................#Coefficient of discharge for air\n",
+    "Cdf=0.7#.....................#Coefficient of discharge for fuel\n",
+    "p1=1.013#.....................#Atmospheric pressure in bar\n",
+    "g=9.81#.......................#Acceleration due to gravity in m/s**2\n",
+    "R=287#........................#Gas constant in J/kg.K\n",
+    "#calculations\n",
+    "mf=pc/3600#....................#Rate of fuel consumption in kg/sec\n",
+    "rhof=spgrp*rhow#...............#Density of fuel in kg/m**3\n",
+    "rhoa=(p1*10**5)/(R*t1)#............#Density of air in kg/m**3\n",
+    "ma=mf*afr#.......................#Air flow rate \n",
+    "delpa=((ma/(Cda*(pi/4)*d2**2))**2)*(1/(2*rhoa))#....................#Suction in N/m**2\n",
+    "df=sqrt((mf/sqrt(2*rhof*(delpa-(g*z*rhof))))*(1/(Cdf*(pi/4))))#.................#Diameter of fuel jet in m\n",
+    "print \"Diameter of the fuel jet = %0.2f mm\"%(df*1000)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 11.4 PAGE 402"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 15,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Suction at the throat = 7.67 cm of Water \n",
+      "Throat area = 2.86 cm \n",
+      "Velocity of air across the venturi throat = 8.34 m/s \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt,pi\n",
+    "# Initialisation of Variables\n",
+    "pc=5.45#......................#Petrol consumption in kg/h\n",
+    "afr=15#......................#Air fuel ratio\n",
+    "af=2*10**(-6)#................#Fuel jet orifice area in m**2\n",
+    "z=0.00635#...................#Distance between tip of fuel jet and level of petrol in the float chamber in m\n",
+    "Cda=0.8#............................#Coefficient of discharge of venturi throat\n",
+    "rhoa=1.29#........................#Density of air in kg/m**3\n",
+    "spgrp=0.72#........................#Specific gravity of fuel\n",
+    "rhow=1000#.........................#Density of water in kg/m**3\n",
+    "g=9.81#..............................#Acceleration due to gravity in m/s**2\n",
+    "Cdf=0.75#........................#Coefficient of discharge of the fuel\n",
+    "#calculations\n",
+    "mf=pc/3600#....................#Fuel consumed in kg/sec\n",
+    "rhof=spgrp*rhow#...............#Density of fuel in kg/m**3\n",
+    "delp=(((mf/(af*Cdf))**2)*(1/(2*rhof)))+(g*z*rhof)#......................#Depression in venturi throat in N/m**2\n",
+    "h2odep=delp/(g*1000)#................................#Depression in venturi throat in cm of Water\n",
+    "print \"Suction at the throat = %0.2f cm of Water \"%(h2odep*100)\n",
+    "ma=mf*afr#................#Air flow rate\n",
+    "At=sqrt(((ma/Cda)**2)*(1/(2*rhoa*delp)))#....................#Throat area in m**2\n",
+    "dt=sqrt(At/(pi/4))#........................................#Throat diameter in m\n",
+    "print \"Throat area = %0.2f cm \"%(dt*100)\n",
+    "Ct=sqrt((2*g*z*rhof)/rhoa)#..........................#Velocity of air across the venturi throat in m/sec\n",
+    "print \"Velocity of air across the venturi throat = %0.2f m/s \"%(Ct)\n"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 11.5 PAGE 403"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 16,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Throat pressure = 0.76 bar \n",
+      "Air fuel ratio when the air cleaner is fitted : 13.69\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt,pi\n",
+    "# Initialisation of Variables\n",
+    "afr=15#.....................#Air fuel ratio\n",
+    "p1=1#.........................#Atmospheric pressure in bar\n",
+    "p2=0.8#.......................#Pressure at venturi throat in bar\n",
+    "pd=30#....................#Pressure drop to air cleaner in mm of Hg\n",
+    "rhohg=13600#....................#Density of Hg in kg/m**3\n",
+    "af=240#........................#Air flow at sea level in kg/h\n",
+    "g=9.81#.....................#Acceleration due to gravity in m/s**2\n",
+    "#calculations\n",
+    "delpa=p1-p2#........................#When there is no air cleaner\n",
+    "pt=1-(rhohg*g*(pd/1000)*10**(-5))-delpa#..........................#Throat pressure in bar\n",
+    "print \"Throat pressure = %0.2f bar \"%pt\n",
+    "afrn=afr*sqrt(delpa/(p1-pt))#...............................#Air fuel ratio when the air cleaner is fitted\n",
+    "print \"Air fuel ratio when the air cleaner is fitted : %0.2f\"%afrn"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 11.6 PAGE 403"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 17,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Throat diameter = 0.03 m\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt,pi\n",
+    "# Initialisation of Variables\n",
+    "As=4.6#........................#Air supply in kg/min\n",
+    "p1=1.013#.......................#Atmospheric pressure in bar\n",
+    "t1=298#......................#Atmospheric temperature in Kelvin\n",
+    "C2=80#........................#Air flow velocity in m/s\n",
+    "Cv=0.8#....................#Velocity co efficient\n",
+    "ga=1.4#........................#Degree of freedom of gas\n",
+    "R=0.287#........................#Gas constant in kJ/kgK\n",
+    "#Calculations\n",
+    "cp=R*(ga/(ga-1))#.......................#Specific heat capacity of air in kJ/kgK\n",
+    "p2=((1-(((C2/Cv)**2)*(1/(2*cp*1000*t1))))**(ga/(ga-1)))*p1#...................#Throat pressure in bar\n",
+    "rho1=(p1*10**5)/(R*1000*t1)#\n",
+    "rho2=rho1*(p2/p1)**(1/ga)#\n",
+    "ma=As/60#...................#Air flow in kg/s\n",
+    "A2=ma/(rho2*C2)#.................#Throat area in m**2\n",
+    "d2=sqrt((4*A2)/pi)#................#Throat diameter in m\n",
+    "print \"Throat diameter = %0.2f m\"%d2"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 11.7 PAGE 404"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 18,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Throat diameter = 3.53 cm \n",
+      "Orifice diameter = 0.0023 cm \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt,pi\n",
+    "# Initialisation of Variables\n",
+    "As=6#........................#Air supply in kg/min\n",
+    "fs=0.45#..........................#Fuel supply in kg/min\n",
+    "p1=1.013#.......................#Atmospheric pressure in bar\n",
+    "t1=300#......................#Atmospheric temperature in Kelvin\n",
+    "rhof=740#......................#Density of fuel in kg/m**3\n",
+    "C2=92#........................#Air flow velocity in m/s\n",
+    "Cda=0.8#....................#Velocity co efficient\n",
+    "Cdf=0.6#.........................#Coefficient of discharge for fuel\n",
+    "ga=1.4#........................#Degree of freedom of gas\n",
+    "r=0.75#......................#ratio of pressure drop across venturi and of that of choke\n",
+    "R=0.287#........................#Gas constant in kJ/kgK\n",
+    "#Calculations\n",
+    "ma=As/60#.................................#Air flow in kg/s\n",
+    "mf=fs/60#.................................#Fuel flow in kg/s\n",
+    "cp=R*(ga/(ga-1))#.......................#Specific heat capacity of air in kJ/kgK\n",
+    "p2=((1-(((C2/Cda)**2)*(1/(2*cp*1000*t1))))**(ga/(ga-1)))*p1#...................#Throat pressure in bar\n",
+    "v1=(R*t1*1000)/(p1*10**5)#\n",
+    "v2=v1*(p1/p2)**(1/ga)#................#specific volume in m**3/kg\n",
+    "A2=(ma*v2)/(C2)#.................#Throat area in m**2\n",
+    "d2=sqrt((4*A2)/pi)#................#Throat diameter in m\n",
+    "print \"Throat diameter = %0.2f cm \"%(d2*100)\n",
+    "pdv=p1-p2#..........#Pressure drop at venturi in bar\n",
+    "pdj=r*pdv#.............#Pressure drop at jet in bar\n",
+    "Af=((mf/Cdf)*(1/sqrt(2*rhof*pdj*10**5)))#.............#Area of orifice in m**2\n",
+    "df=sqrt((4*Af)/pi)#................#Orifice diameter in m\n",
+    "print \"Orifice diameter = %0.4f cm \"%(df)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 11.8 PAGE 404"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 7,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Diameter of choke = 29.61 mm \n",
+      "Diameter of the fuel jet = 1.68 mm \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt,pi\n",
+    "# Initialisation of Variables\n",
+    "Vs=1489*10**(-6)#.......................#Capacity of engine in m**3\n",
+    "N=4200#...............#Engine rpm at which max speed is developed\n",
+    "etaV=0.75#.....................#Volumetric efficiency\n",
+    "afr=13#........................#air fuel ratio\n",
+    "Ct=85#..........................#Theoretical air speed at peak power in m/s\n",
+    "C2=Ct#\n",
+    "Cda=0.82#....................#Coefficient of discharge for the venturi\n",
+    "Cdf=0.65#....................#Coefficient of discharge of main petrol jet\n",
+    "spgr=0.74#..................#Specific gravity of petrol\n",
+    "z=0.006#.................................#Level of petrol surface below choke\n",
+    "p1=1.013#......................#Atmospheric pressure in bar\n",
+    "t1=293#.........................#Atmospheric temperature in Kelvin\n",
+    "r=0.4#.............................#Ratio of diameter of emulsion tube to choke diameter\n",
+    "R=0.287#.............................#Gas constant in kJ/kgK\n",
+    "ga=1.4#..............................#Degree of freedom for air\n",
+    "g=9.81#..............................#Acceleration due to gravity in m/s**2\n",
+    "rhow=1000#...........................#Density of water in kg/m**3\n",
+    "#calculations\n",
+    "rhof=rhow*spgr#............................#Density of fuel in kg/m**3\n",
+    "Va=(etaV*Vs*N)/(60*2)#.....................#Volume of air induced in m**3/s\n",
+    "ma=(p1*10**5*Va)/(R*t1*1000)#...............#mass flow of air in kg/s\n",
+    "cp=R*(ga/(ga-1))#.......................#Specific heat capacity of air in kJ/kgK\n",
+    "p2=((1-(((C2)**2)*(1/(2*cp*1000*t1))))**(ga/(ga-1)))*p1#...................#Throat pressure in bar\n",
+    "pt=p2#\n",
+    "vt=Va*(p1/p2)**(1/ga)#.....................#Volume flow of air at choke in m**3/s\n",
+    "At=vt/(Ct*Cda)#...................#Area of emulsion tube in m\n",
+    "D=sqrt((4*At*10**6)/(pi*(1-r**2)))#...................#Diameter of choke in mm\n",
+    "print \"Diameter of choke = %0.2f mm \"%D\n",
+    "mf=ma/afr#..................#Mass flow of fuel in kg/s\n",
+    "delpa=(p1-p2)*10**5#\n",
+    "df=sqrt((mf/sqrt(2*rhof*(delpa-(g*z*rhof))))*(1/(Cdf*(pi/4))))#.................#Diameter of fuel jet in m\n",
+    "print \"Diameter of the fuel jet = %0.2f mm \"%(df*1000)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 11.9 PAGE 405"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 6,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Air fuel ratio when the nozzle lip is neglected :  11.35\n",
+      "Air fuel ratio when nozzle lip is taken into account :  11.39\n",
+      "Minimum velocity of air = 8.58 m/s\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt,pi\n",
+    "# Initialisation of Variables\n",
+    "da=0.018#..........................#Throat Diameter in m\n",
+    "df=0.0012#......................#Diameter of fuel orifice in m\n",
+    "Cda=0.82#.................#Coefficient of air flow\n",
+    "Cdf=0.65#......................#Coefficient of fuel flow\n",
+    "z=0.006#........................#Level of petrol surface below the throat\n",
+    "rhoa=1.2#.......................#density of air in kg/m**3\n",
+    "rhof=750#.........................#density of fuel in kg/m**3\n",
+    "g=9.81#........................#Acceleration due to gravity in m/s**2\n",
+    "delp=0.065*10**5#...................#Pressure drop in N/m**2\n",
+    "#Calculations\n",
+    "afr1=(Cda/Cdf)*((da/df)**2)*sqrt(rhoa/rhof)#..................#Air fuel ratio when the nozzle lip is neglected\n",
+    "print \"Air fuel ratio when the nozzle lip is neglected : \",round(afr1,2)\n",
+    "afr2=afr1*sqrt(delp/(delp-(g*z*rhof)))#.....................#Air fuel ratio when nozzle lip is taken into account\n",
+    "print \"Air fuel ratio when nozzle lip is taken into account : \",round(afr2,2)\n",
+    "C2=sqrt((2*g*z*rhof)/rhoa)#.........................#Minimum velocity of air in m/s\n",
+    "print \"Minimum velocity of air = %0.2f m/s\"%C2"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 11.10 PAGE 406"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 5,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Fuel consumption = 46.66 kg/h \n",
+      "Velocity of air at the throat = 132.52 m/s \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt,pi\n",
+    "# Initialisation of Variables\n",
+    "d=0.11#..................#Engine bore in m\n",
+    "l=0.11#..................#Engine length in m\n",
+    "da=0.042#................#Throat diameter of the choke tube in m\n",
+    "N=3000#..................#Engine rpm\n",
+    "etaV=0.75#...............#Volumetric efficiency\n",
+    "Ra=287#..................#Gas constant for air in J/kgK\n",
+    "Rv=97#...................#Gas constant for fuel vapour in J/kgK\n",
+    "t=273#....................#Temperature in Kelvin\n",
+    "p=1.013#...................#Pressure in bar\n",
+    "delpa=0.12#.................#Pressure depression in bar\n",
+    "t2=273+15#...................#Temperature at throat\n",
+    "n=8#........................#No of cylinders\n",
+    "mO=32#.......................#Mass of Oxygen molecule in amu\n",
+    "mC=12#........................#Mass of Carbon molecule in amu\n",
+    "mH=1#.......................#Mass of Hydrogen molecule in amu\n",
+    "cC=84#......................#Composition of carbon in %\n",
+    "cH2=16#.....................#Composition of Hydrogen in % \n",
+    "#Calculations\n",
+    "Vfm=(pi/4)*d*d*l*n*(N/2)*etaV#.....................#Volume of fuel mixture supplied in m**3/min\n",
+    "afr=((cC*(mO/mC))+(cH2*(mO/(4*mH))))/23#..................#Air fuel ratio\n",
+    "va=(Ra*t)/(p*10**5)#.....................#Volume of 1 kg of air in m**3/kg\n",
+    "vf=(Rv*t)/(p*10**5)#......................#Volume of 1 kg of fuel vapour in m**3/kg\n",
+    "fc=(Vfm/((afr*va)+vf))*60#...............#Fuel consumption in kg/h\n",
+    "print \"Fuel consumption = %0.2f kg/h \"%fc\n",
+    "rhoa=((p-delpa)*10**5)/(Ra*t2)#...............#Density of air at the throat in kg/m**3\n",
+    "Ca=(afr*(fc/3600))/((pi/4)*da*da*rhoa)#................#Velocity of air at the throat in m/s\n",
+    "print \"Velocity of air at the throat = %0.2f m/s \"%Ca"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 11.11 PAGE 407"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 4,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Air fuel ratio at the altitude : 11.26\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt,pi\n",
+    "# Initialisation of Variables\n",
+    "a=4500#.................#Altitude\n",
+    "afr=14#...............#Air fuel ratio at sea level\n",
+    "t1=25#...........#Temperature at sea level in Celsius\n",
+    "p1=1.013#...........#Pressure at sea level in bar\n",
+    "#Calculations\n",
+    "t2=t1-(0.0064*a)#.........................#Temperature at the given altitude using the given formula in Celsius\n",
+    "p2=p1/(10**(a/19300))#....................#Pressure at the given altitude using the given formula in bar\n",
+    "afr2=afr*sqrt((p2*(t1+273))/(p1*(t2+273)))#...................#Air fuel ratio at the altitude\n",
+    "print \"Air fuel ratio at the altitude : %0.2f\"%afr2"
+   ]
+  }
+ ],
+ "metadata": {
+  "kernelspec": {
+   "display_name": "Python 2",
+   "language": "python",
+   "name": "python2"
+  },
+  "language_info": {
+   "codemirror_mode": {
+    "name": "ipython",
+    "version": 2
+   },
+   "file_extension": ".py",
+   "mimetype": "text/x-python",
+   "name": "python",
+   "nbconvert_exporter": "python",
+   "pygments_lexer": "ipython2",
+   "version": "2.7.9"
+  }
+ },
+ "nbformat": 4,
+ "nbformat_minor": 0
+}
diff --git a/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER12_2.ipynb b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER12_2.ipynb
new file mode 100644
index 00000000..36e5f2df
--- /dev/null
+++ b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER12_2.ipynb
@@ -0,0 +1,445 @@
+{
+ "cells": [
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "# CHAPTER-12 Fuel injection systems for C.I. Engines "
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 12.1 PAGE 421"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 4,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Volume of Fuel Injected per Cycle = 0.05 cc \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "\n",
+    "n=6#...............#No of cylinders\n",
+    "BP=125#...............#Brake Power in kW\n",
+    "N=3000#..............#Engine rpm\n",
+    "bsfc=200#............#Brake Specific Fuel Consumption g/kWh\n",
+    "spgr=0.85#.............#Specific Gravity\n",
+    "\n",
+    "#Calculations\n",
+    "\n",
+    "fc=(bsfc/1000)*BP#.........#Fuel consumption in kg/h\n",
+    "fcpc=fc/n#..................#Fuel consumption per cylinder\n",
+    "FCPC=(fcpc/60)/(N/2)#................#Fuel Consumption per cycle in kg\n",
+    "VFIC = (FCPC*1000)/spgr#...................#Volume of fuel injected per cycle in cc\n",
+    "print \"Volume of Fuel Injected per Cycle = %0.2f cc \"%VFIC"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 12.2 PAGE 421"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 11,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Diameter of Nozzle Orifice = 8.13e-04 m \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt, pi\n",
+    "# Initialisation of Variables\n",
+    "n=6#...............#No of cylinders\n",
+    "N=1500#............#Engine rpm\n",
+    "BP=220#.............#Brake Power in kW\n",
+    "bsfc=0.273#..........#Brake Specific Fuel Consumption in kg/kWh\n",
+    "theta=30#.............#The Period of Injection in degrees of crank angle\n",
+    "spgr=0.85#............#Specific Gravity of fuel\n",
+    "Cf=0.9#................#Orifice discharge co-efficient\n",
+    "ip=160#...............#Injection pressure in bar\n",
+    "cp=40#.................#Pressure in combustion chamber in bar\n",
+    "rhow=1000#................#Density of water in kg/m**3\n",
+    "#Calculations\n",
+    "vf = Cf*sqrt((2*(ip-cp)*10**5)/(spgr*rhow))#.............#Actual fuel velocity of injection in m/sec\n",
+    "qf=(bsfc*BP)/(spgr*rhow*3600)#..................# Volume of fuel injected per sec in m**3\n",
+    "d=sqrt (qf/((pi/4)*n*vf*(theta/360)*(60/N)*(N/120)))#...........#Diameter of nozzle orifice\n",
+    "print \"Diameter of Nozzle Orifice = %0.2e m \"%d"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 12.3 PAGE 422"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 12,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Volume of Fuel Injected per Cycle = 0.13 cm**3 \n",
+      "Diameter of orifice = 0.40 mm \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt, pi\n",
+    "# Initialisation of Variables\n",
+    "n=1#............#No of cylinders\n",
+    "N=650#............#Engine rpm\n",
+    "theta=28#...........#Crank Travel in degree\n",
+    "fc=2.2#...........#Fuel consumption in kg/h\n",
+    "spgr=0.875#............#Specific Gravity\n",
+    "ip=150#................#Injection Pressure in bar\n",
+    "cp=32#.................#Combustion chamber Pressure in bar\n",
+    "Cd=0.88#...............#co-efficient of discharge of orifice\n",
+    "rhow=1000#...........#Density of water in kg/m**3\n",
+    "#Calculation\n",
+    "fcpc = fc/60#..............#Fuel consumption per cylinder\n",
+    "fipc = fcpc/(N/2)#.........#Fuel Injected per cycle in kg\n",
+    "vfpc = fipc/(spgr*rhow)#....#volume of fuel injected per cycle\n",
+    "print \"Volume of Fuel Injected per Cycle = %0.2f cm**3 \"%(vfpc*10**6)\n",
+    "tfic=(theta/360)*(60/N)#....#Time for Fuel Injection per Cycle in sec\n",
+    "mf = fipc/tfic#...............#Mass of fuel injected per cycle in kg/s\n",
+    "vf = Cd*sqrt((2*(ip-cp)*10**5)/(spgr*rhow))#.............#Actual fuel velocity of injection in m/sec\n",
+    "d=sqrt((mf*4)/(pi*vf*spgr*rhow))\n",
+    "print \"Diameter of orifice = %0.2f mm \"%(d*1000)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 12.4 PAGE 423"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 13,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Diameter of orifice = 0.56 mm \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt, pi\n",
+    "# Initialisation of Variables\n",
+    "N=2000#............#Engine rpm\n",
+    "theta=30#...........#Crank Travel in degree\n",
+    "sfc=0.272#...........#Fuel consumption in kg/kWh\n",
+    "ip=120#................#Injection Pressure in bar\n",
+    "cp=30#.................#Combustion chamber Pressure in bar\n",
+    "Cd=0.9#...............#co-efficient of discharge of orifice\n",
+    "rhow=1000#...........#Density of water in kg/m**3\n",
+    "api = 32#..............#API in degree\n",
+    "pw=15#..................#Power Output in kW\n",
+    "#Calculation\n",
+    "spgr= 141.5/(131.5+api)#............#Specific Gravity\n",
+    "fcpc = (sfc*pw)/((N/2)*60)#..............#Fuel consumption per cycle in kg\n",
+    "tfic=(theta/360)*(60/N)#....#Time for Fuel Injection per Cycle in sec\n",
+    "mf = fcpc/tfic#...............#Mass of fuel injected per cycle in kg/s\n",
+    "vf = Cd*sqrt((2*(ip-cp)*10**5)/(spgr*rhow))#.............#Actual fuel velocity of injection in m/sec\n",
+    "d=sqrt((mf*4)/(pi*vf*spgr*rhow))\n",
+    "print \"Diameter of orifice = %0.2f mm \"%(d*1000)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 12.5 PAGE 424"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 14,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Fuel consumption = 0.28 kg/kWh \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt, pi\n",
+    "# Initialisation of Variables\n",
+    "N=1800#............#Engine rpm\n",
+    "theta=32#...........#Crank Travel in degree\n",
+    "ip=118.2#................#Injection Pressure in bar\n",
+    "cp=31.38#.................#Combustion chamber Pressure in bar\n",
+    "Cd=0.9#...............#co-efficient of discharge of orifice\n",
+    "rhow=1000#...........#Density of water in kg/m**3\n",
+    "api = 32#..............#API in degree\n",
+    "pw=11#..................#Power Output in kW\n",
+    "d=0.47#...................#Fuel Injection orifice diameter in mm\n",
+    "#Calculation\n",
+    "spgr= 141.5/(131.5+api)#............#Specific Gravity\n",
+    "tfic=(theta/360)*(60/N)#....#Time for Fuel Injection per Cycle in sec\n",
+    "vf = Cd*sqrt((2*(ip-cp)*10**5)/(spgr*rhow))#.............#Actual fuel velocity of injection in m/sec\n",
+    "mf=vf*spgr*rhow*(pi/4)*(d/1000)**2#\n",
+    "tncp=(N/2)*60#...............#Total no of cycles per hour\n",
+    "FIPC=mf*tfic#.................#Mass of fuel injected per cycle in kg/cycle\n",
+    "fc=FIPC*tncp*(1/pw)#...................#Fuel consumption in kg/kWh\n",
+    "print \"Fuel consumption = %0.2f kg/kWh \"%fc"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 12.6 PAGE 424"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 15,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Orifice Area Required per injector = 0.0136 cm**2 \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt, pi\n",
+    "# Initialisation of Variables\n",
+    "n=8#......#No of cylinders\n",
+    "pw=386.4#...........#Power output in kW\n",
+    "N=800#.............#Engine rpm\n",
+    "fc=0.25#.............#Fuel Consumption in kg/kWh\n",
+    "theta=12#..............#Crank Travel in degree (for injection)\n",
+    "spgr=0.85#...........#Specific Gravity\n",
+    "patm=1.013#............#Atmospheric pressure\n",
+    "cf=0.6#................#Co-efficient of discharge for injector\n",
+    "pcB=32#................#Pressure in cylinder in beginning in bar\n",
+    "piB=207#...............#Pressure in injector in beginning in bar\n",
+    "pcE=55#...............#Pressure in cylinder at the end in bar\n",
+    "piE=595#................#Pressure in injector at the end in bar\n",
+    "rhow=1000#..............#density of water in kg/m**3\n",
+    "#calculations\n",
+    "pwpc = pw/n#......................#Output per cylinder\n",
+    "fcpc = (pwpc*fc)/60#.............#Fuel consumption per cylinder in kg/min\n",
+    "fipc = fcpc/(N/2)#................#Fuel injected per cycle in kg\n",
+    "tfic = (theta*60)/(360*N)#...........#Time for fuel Injection per cycle\n",
+    "mf = fipc/tfic#......................#Mass of fuel injected per second\n",
+    "pdb = piB-pcB#....................#Pressure difference at beginning\n",
+    "pde = piE-pcE#...................#Pressure difference at end\n",
+    "apd = (pdb+pde)/2#\n",
+    "Ao=mf/(cf*sqrt(2*apd*10**5*spgr*rhow))#\n",
+    "print \"Orifice Area Required per injector = %0.4f cm**2 \"%(Ao*10000)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 12.7 PAGE 425"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 16,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The mass of fuel injected into each cylinder per second = 1.10 kg/s\n",
+      "Diameter of the fuel orifice = 0.55 mm \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt, pi\n",
+    "# Initialisation of Variables\n",
+    "n=6#...............#No of cylinders\n",
+    "afr=20#...........#Air fuel ratio\n",
+    "d = 0.1#...............#cylinder bore in mm\n",
+    "l=0.14#..............#Cylinder length in mm\n",
+    "etav=0.8#............#Volumetric Efficiency\n",
+    "pa=1#.................#Pressure at the beginning of the compression in bar\n",
+    "ta = 300#.............#Temperature at the beginning of the compression in Kelvin\n",
+    "theta = 20#...............#Crank travel in degree for injection\n",
+    "N = 1500#...................#engine rpm\n",
+    "rhof=960#.................#Fuel density in kg/m**3\n",
+    "cf=0.67#................#Co efficient of discharge for injector\n",
+    "pi=150#....................#injection pressure in bar\n",
+    "pc=40#....................#combustion pressure in bar\n",
+    "R=287#........................#gas constant for air in kJ/kg.K\n",
+    "#calculations\n",
+    "V=(pi/4)*d**2*l*etav#......................#Volume of air supplied per cylinder per cycle in m**3\n",
+    "ma=(pa*10**5*V)/(R*ta)#.....................#Mass of this air at suction conditions in kg/cycle\n",
+    "mf=ma/afr#............................#Mass of fuel in kg/cycle\n",
+    "fipc = (theta*60)/(360*N)#...........#Time taken for fuel injection per cycle in seconds\n",
+    "MF = mf/fipc#........................#Mass of fuel injected into each cylinder per second\n",
+    "print \"The mass of fuel injected into each cylinder per second = %0.2f kg/s\"%MF\n",
+    "vf=cf*sqrt((2*(pi-pc)*10**5)/rhof)#.............#fuel velocity injection in m/s\n",
+    "d0=sqrt((MF*4)/(pi*vf*rhof))#..................#diameter of fuel orifice in m\n",
+    "print \"Diameter of the fuel orifice = %0.2f mm \"%(d0*1000)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 12.8 PAGE 425"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 17,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Total displacement of plunger = 0.26 cc\n",
+      "Effective stroke of plunger = 0.69 mm \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt, pi\n",
+    "# Initialisation of Variables\n",
+    "Vpbes=7#.................#Volume of fuel in the pump barrel before commencement of effective stroke in cc\n",
+    "df=3#.................#Diameter of fuel line from pump to injector in mm\n",
+    "lf=700#.................#Length of fuel line from pump to injector in mm\n",
+    "Vfiv=2#................#Volume of fuel in the injection valve in cc\n",
+    "Vfd=0.1#.................#Volume of fuel to be delivered in cc\n",
+    "p1=150#..............#Pressure at which fuel is delivered in bar\n",
+    "p2=1#.................#atmospheric pressure in bar\n",
+    "cc=78.8*10**(-6)#..........#Co - efficient of compressibility per bar\n",
+    "dp=7#..............#Diameter of plunger in mm\n",
+    "#calculations\n",
+    "V1=Vpbes+(pi/4)*((df/10)**2)*(lf/10)+Vfiv#...................#Total initial fuel volume\n",
+    "delV=cc*(p1-p2)*V1#................#Change in volume due to compression\n",
+    "displu=delV+Vfd#.....................#Total displacement of plunger\n",
+    "print \"Total displacement of plunger = %0.2f cc\"%displu\n",
+    "lp=(displu*4)/(pi*(dp/10)**2)#.............#Effective stroke of plunger\n",
+    "print \"Effective stroke of plunger = %0.2f mm \"%lp"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 12.9 PAGE 426"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 18,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The time required for spray penetration at an injection pressure of 235 bar = 11.98 milliseconds:\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt, pi\n",
+    "# Initialisation of Variables\n",
+    "p1=145#...........#injection pressure in bar\n",
+    "p2=235#.........#Injection pressure in bar (2nd case)\n",
+    "t1=16#.............#spray penetration time in milliseconds\n",
+    "s1=22#................#spray penetration length in cm\n",
+    "s2=22#.................#spray penetration length in cm (2nd case)\n",
+    "pc=30#.................#combustion chamber pressure in bar\n",
+    "#calculations\n",
+    "delp1=p1-pc#\n",
+    "delp2=p2-pc#\n",
+    "t2=(s2/s1)*t1*sqrt(delp1/delp2)#..........#Spray time in seconds for 2nd case\n",
+    "#Given that s=t*sqrt(delp)\n",
+    "print \"The time required for spray penetration at an injection pressure of 235 bar = %0.2f milliseconds:\"%t2"
+   ]
+  }
+ ],
+ "metadata": {
+  "kernelspec": {
+   "display_name": "Python 2",
+   "language": "python",
+   "name": "python2"
+  },
+  "language_info": {
+   "codemirror_mode": {
+    "name": "ipython",
+    "version": 2
+   },
+   "file_extension": ".py",
+   "mimetype": "text/x-python",
+   "name": "python",
+   "nbconvert_exporter": "python",
+   "pygments_lexer": "ipython2",
+   "version": "2.7.9"
+  }
+ },
+ "nbformat": 4,
+ "nbformat_minor": 0
+}
diff --git a/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER15_2.ipynb b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER15_2.ipynb
new file mode 100644
index 00000000..2a5367b8
--- /dev/null
+++ b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER15_2.ipynb
@@ -0,0 +1,76 @@
+{
+ "cells": [
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "# CHAPTER 15 - Engine Cooling"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 15.1 PAGE 499"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 1,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The mass of cooling water required = 3668.50 kg/h for petrol engine \n",
+      "The mass of cooling water required = 2674.95 kg/h for diesel engine \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "BP=90#.................#Brake Power in kW\n",
+    "deltw=27#.................#Raise in temperature of water \n",
+    "etaP=0.25#...................#Efficiency of petrol engine\n",
+    "etaD=0.3#....................#Efficiency od diesel engine\n",
+    "Pec=32#......................#Percentage of energy going to coolant in petrol engine\n",
+    "Dec=28#......................#Percentage of energy going to coolant in diesel engine\n",
+    "cp=4.187#..........#specific heat of water at constant pressure\n",
+    "#Calculations\n",
+    "hsP = BP/etaP#............#Heat supplied in kW or kJ/s\n",
+    "ecP=hsP*(Pec/100)#.............#Energy going to cooling water in kg/s\n",
+    "mwP=ecP/(cp*deltw)#.............#Mass of cooling water required\n",
+    "hsD = BP/etaD#............#Heat supplied in kW or kJ/s\n",
+    "ecD=hsD*(Dec/100)#.............#Energy going to cooling water in kg/s\n",
+    "mwD=ecD/(cp*deltw)#.............#Mass of cooling water required\n",
+    "print \"The mass of cooling water required = %0.2f kg/h for petrol engine \"%(mwP*3600)\n",
+    "print \"The mass of cooling water required = %0.2f kg/h for diesel engine \"%(mwD*3600)"
+   ]
+  }
+ ],
+ "metadata": {
+  "kernelspec": {
+   "display_name": "Python 2",
+   "language": "python",
+   "name": "python2"
+  },
+  "language_info": {
+   "codemirror_mode": {
+    "name": "ipython",
+    "version": 2
+   },
+   "file_extension": ".py",
+   "mimetype": "text/x-python",
+   "name": "python",
+   "nbconvert_exporter": "python",
+   "pygments_lexer": "ipython2",
+   "version": "2.7.9"
+  }
+ },
+ "nbformat": 4,
+ "nbformat_minor": 0
+}
diff --git a/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER16_2.ipynb b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER16_2.ipynb
new file mode 100644
index 00000000..d86cda95
--- /dev/null
+++ b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER16_2.ipynb
@@ -0,0 +1,306 @@
+{
+ "cells": [
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "# CHAPTER 16 - Supercharging of IC Engines"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 16.1 PAGE 525"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 7,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The Power required to run the supercharger = 90.47 kW \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "pwu=735#............#Power developed by naturally aspirated engine in kW\n",
+    "afru=12.8#.............#Air fuel ratio for naturally aspirated engine\n",
+    "bsfc=0.350#......#Brake specific fuel consumption in kg/kWh\n",
+    "metau=0.86#...........#Mechanical efficiency of naturally aspirated engine\n",
+    "pi=730#...........#Inlet pressure in mm of Hg absolute\n",
+    "tm=325#...........#Mixture temperature in Kelvin\n",
+    "pr=1.6#.............#Pressure ratio of supercharged engine\n",
+    "etaa=0.7#.............#Adiabatic efficiency of supercharged engine\n",
+    "metas=0.9#..............#Mechanical efficiency of supercharged engine\n",
+    "afrs=12.8#.............#Air fuel ratio for supercharged engine\n",
+    "rhohg=13600#.............#Density of mercury in kg/m**3\n",
+    "R=0.287#...................#Gas constant in kJ/kgK\n",
+    "ga=1.4#................#Degree of freedom for gas\n",
+    "cp=1.005#..................#Specific heat of the fuel\n",
+    "g=9.81#................#Acceleration due to gravity in m/s**2\n",
+    "#calculations\n",
+    "t2=tm*(pr)**((ga-1)/ga)#..............#Ideal temperature for the supercharged engine\n",
+    "t2a=tm+(t2-tm)/etaa#................#Actual temperature for the supercharged engine\n",
+    "wa=cp*(t2a-tm)#.....................#Work of the supercharger\n",
+    "wsup=cp*(t2a-tm)/metas#..............#Work required to drive the supercharger in kJ/kg of air\n",
+    "#When unsupercharged\n",
+    "p1=(pi/1000)*((g*rhohg)/1000)#..............#Inlet pressure in kN/m**2\n",
+    "rhounsup=p1/(R*tm)#\n",
+    "maunsup=(bsfc*pwu*afrs)/3600#...................#Air consumption in kg/s for unsupercharged engine\n",
+    "#When supercharged\n",
+    "rhosup=(pr*p1)/(R*t2a)#\n",
+    "masup=maunsup*(rhosup/rhounsup)#..................#Air consumption in kg/s\n",
+    "Psup=masup*wsup#...............#Power required to run the supercharger in kW\n",
+    "print \"The Power required to run the supercharger = %0.2f kW \"%Psup"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 16.2 PAGE 526"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 1,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The Engin Capacity = 0.02 m**3 \n",
+      "The Brake mean effective pressure  = 8.34 bar\n",
+      "The Increase of pressure required = 0.47 bar\n"
+     ]
+    }
+   ],
+   "source": [
+    "# Initialisation of Variables\n",
+    "p1=1.0132#..............#Mean pressure at sea level in bar\n",
+    "t1=283#................#Mean temperature at sea level in Kelvin\n",
+    "BP=260#....................#Brake Power output in kW\n",
+    "etaV=0.78#..................#Volumetric efficiency at sea level free air condition\n",
+    "sfc=0.247#............#Specific Fuel consumption in kg/kW.h\n",
+    "afr=17#...................#Air fuel ratio\n",
+    "N=1500#...................#Engine rpm\n",
+    "at=2700#.................#Altitude in mts\n",
+    "p2=0.72#................#Pressure in bar at the given altitude\n",
+    "Psup=0.08#.................#8% power of engine is taken by the supercharger\n",
+    "R=287#...................#Gas constant in J/kgK\n",
+    "t2=32+273#..............#Temperature in Kelvin at the given altitude\n",
+    "#calculations\n",
+    "mf=(sfc*BP)/60#.............#Fuel consumption in kg/min\n",
+    "ma = mf*afr#..................#Air consumption in ig/min\n",
+    "acps = ma/(N/2)#............#Air consumption per stroke in kg\n",
+    "Vs=(acps*R*t1)/(etaV*p1*10**5)#................#Engine capacity in m**3\n",
+    "print \"The Engin Capacity = %0.2f m**3 \"%Vs\n",
+    "pmb=(BP*6)/(Vs*10*(N/2))#........#Brake Mean Effective Pressure in bar\n",
+    "print \"The Brake mean effective pressure  = %0.2f bar\"%pmb\n",
+    "gp=BP/(1-Psup)#.................#Gross power produced by supercharged engine in kW\n",
+    "masup=ma*gp/BP#......................#Mass of air required for supercharged engine in kg\n",
+    "matc=masup/(N/2)#..............#Mass of air taken per cycle\n",
+    "pressure=(matc*R*t2)/(etaV*10**5*Vs)#\n",
+    "print \"The Increase of pressure required = %0.2f bar\"%(pressure-p2)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 16.3 PAGE 527"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 2,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The Net increase in Brake Power = 17.60 kW \n"
+     ]
+    }
+   ],
+   "source": [
+    "# Initialisation of Variables\n",
+    "ec=3600*10**(-6)#.............#Engine capacity in m**3\n",
+    "pw=13#...............#Power developed in kW per m**3 of free air induced per minute\n",
+    "etaV=0.82#............#Volumetric Efficiency\n",
+    "N=3000#................#Engine rpm\n",
+    "p1=1.0132#...........................#Initial Air pressure in bar\n",
+    "t1=298#........................#Initial Temperature in Kelvin\n",
+    "pr=1.8#.....................#Pressure ratio in rotary compressor\n",
+    "etaC=0.75#.................#Isentropic efficiency of compressor\n",
+    "etaM=0.8#....................#Mechanical efficiency\n",
+    "ga=1.4#.....................#Degree of freedom for the gas\n",
+    "td=4#.......................#The amount by which the temperature is kess than delivery temperature from compressor\n",
+    "R=287#......................#Gas constant in J/kg.K\n",
+    "cp=1.005#.....................#Specific heat capacity\n",
+    "#Calculations\n",
+    "Vs=(ec*N)/2#....................#Swept volume in m**3/min\n",
+    "Vu=Vs*etaV#....................#Unsupercharged volume induced per min\n",
+    "rcdp=pr*p1#........#Rotary compressor delivery pressure\n",
+    "t2=t1*(pr)**((ga-1)/ga)#..............#Ideal temperature for the supercharged engine\n",
+    "t2a=t1+(t2-t1)/etaC#................#Actual temperature for the supercharged engine\n",
+    "ta=t2a-td#............................#Temperature of air at intake to the engine cylinder\n",
+    "V1=(rcdp*Vs*t1)/(p1*ta)#.................#Equivalent volume at 1.0132 bar and 298 K\n",
+    "Vinc=V1-Vs#...........................#Increase in induced Volume of air in m**3/min\n",
+    "ipincai=pw*Vinc#.......................#Increase in IP from air induced in kW\n",
+    "ipinciip=((rcdp-p1)*10**5*Vs)/(60*1000)#...........#Increase in IP due to increased induction pressure kW\n",
+    "ipinctot=ipincai+ipinciip#...............#Total increase in Input Power in kW\n",
+    "bpinc=ipinctot*etaM#....................#Increase in Brake Power of the engine in kW\n",
+    "ma=(rcdp*10**5*Vs)/(60*R*ta)#...................#Mass of air delivered by the compressor kg/s\n",
+    "pc=(ma*cp*(t2a-t1))/etaM#....................#Power required by the compressor\n",
+    "bpincnet=bpinc-pc#..........................#Net Increase in BP\n",
+    "print \"The Net increase in Brake Power = %0.2f kW \"%bpincnet"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 16.4 PAGE 528"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 3,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The Engine Capacity = 0.02 m**3:\n",
+      "The Brake mean effective pressure = 8.41 bar\n",
+      "The Increase of pressure required = 0.47 bar\n"
+     ]
+    }
+   ],
+   "source": [
+    "# Initialisation of Variables\n",
+    "p1=1.0132#..............#Mean pressure at sea level in bar\n",
+    "t1=283#................#Mean temperature at sea level in Kelvin\n",
+    "BP=250#....................#Brake Power output in kW\n",
+    "etaV=0.78#..................#Volumetric efficiency at sea level free air condition\n",
+    "sfc=0.245#............#Specific Fuel consumption in kg/kW.h\n",
+    "afr=17#...................#Air fuel ratio\n",
+    "N=1500#...................#Engine rpm\n",
+    "at=2700#.................#Altitude in mts\n",
+    "p2=0.72#................#Pressure in bar at the given altitude\n",
+    "Psup=0.08#.................#8% power of engine is taken by the supercharger\n",
+    "R=287#...................#Gas constant in J/kgK\n",
+    "t2=32+273#..............#Temperature in Kelvin at the given altitude\n",
+    "#calculations\n",
+    "mf=(sfc*BP)/60#.............#Fuel consumption in kg/min\n",
+    "ma = mf*afr#..................#Air consumption in ig/min\n",
+    "acps = ma/(N/2)#............#Air consumption per stroke in kg\n",
+    "Vs=(acps*R*t1)/(etaV*p1*10**5)#................#Engine capacity in m**3\n",
+    "print \"The Engine Capacity = %0.2f m**3:\"%Vs\n",
+    "pmb=(BP*6)/(Vs*10*(N/2))#........#Brake Mean Effective Pressure in bar\n",
+    "print \"The Brake mean effective pressure = %0.2f bar\"%pmb\n",
+    "gp=BP/(1-Psup)#.................#Gross power produced by supercharged engine in kW\n",
+    "masup=ma*gp/BP#......................#Mass of air required for supercharged engine in kg\n",
+    "matc=masup/(N/2)#..............#Mass of air taken per cycle\n",
+    "pressure=(matc*R*t2)/(etaV*10**5*Vs)#\n",
+    "print \"The Increase of pressure required = %0.2f bar\"%(pressure-p2)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 16.5 PAGE 529"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 4,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The indicated mean effective pressure = 4.55 bar \n",
+      "The total aspirated air mass flow into the engine = 6.73 kg/min \n",
+      "Air flow into the compressor = 16.79 kg/min\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "t1=298#.................#Temperature of the air while entering the compressor in Kelvin\n",
+    "qrej=1210#..............#Amount of heat rejected in cooler in kJ/min\n",
+    "t2=273+65#...............#Temperature of the air leaving the cooler in Kelvin\n",
+    "p2=1.75#.................#Pressure of the air leaving the cooler in bar\n",
+    "n=6#.....................#No of cylinders\n",
+    "d=0.1#...................#Bore of the cylinder in m\n",
+    "l=0.11#...................#Stroke of the cylinder in m\n",
+    "etaV=0.72#................#volumetric efficiency\n",
+    "N=2000#...............#Engine rpm\n",
+    "Tout=150#..................#Torque Output in Nm\n",
+    "etaM=0.8#..................#Mechanical efficiency\n",
+    "R=287#.......................#Gas constant for air in J/kgK\n",
+    "cp=1.005#...................#Specific capacity of air\n",
+    "#calculations\n",
+    "BP=(2*pi*N*Tout)/(60*1000)#...........#Brake power in kW\n",
+    "IP=BP/etaM#..........#Input Power in kW\n",
+    "Vc=(pi/4)*d*d*l#...................#Cylinder Volume in m**3\n",
+    "pmi=(6*IP)/(n*Vc*(N/2)*10)#................#Indicated mean effective pressure\n",
+    "print \"The indicated mean effective pressure = %0.2f bar \"%(pmi)\n",
+    "Vs=Vc*6*(N/2)#.........................#Engine Swept Volume in m**3/min\n",
+    "Vaa=Vs*etaV#..........................#Aspirated volume of air into engine in m**3/min\n",
+    "maa=(p2*10**5*Vaa)/(R*t2)#..............#Aspirated air mass flow into the engine in kg/min\n",
+    "print \"The total aspirated air mass flow into the engine = %0.2f kg/min \"%maa\n",
+    "t2a=((((BP/cp)/(qrej/(60*cp)))*t2)-t1)/(((BP/cp)/(qrej/(60*cp)))-1)#\n",
+    "mc=((BP/cp)/(t2a-t1))*60#........................#Air flow into the compressor in kg/min\n",
+    "print \"Air flow into the compressor = %0.2f kg/min\"%mc"
+   ]
+  }
+ ],
+ "metadata": {
+  "kernelspec": {
+   "display_name": "Python 2",
+   "language": "python",
+   "name": "python2"
+  },
+  "language_info": {
+   "codemirror_mode": {
+    "name": "ipython",
+    "version": 2
+   },
+   "file_extension": ".py",
+   "mimetype": "text/x-python",
+   "name": "python",
+   "nbconvert_exporter": "python",
+   "pygments_lexer": "ipython2",
+   "version": "2.7.9"
+  }
+ },
+ "nbformat": 4,
+ "nbformat_minor": 0
+}
diff --git a/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER17_2.ipynb b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER17_2.ipynb
new file mode 100644
index 00000000..d2517e96
--- /dev/null
+++ b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER17_2.ipynb
@@ -0,0 +1,2533 @@
+{
+ "cells": [
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "# CHAPTER 17 - Testing and performance of I.C. engines"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.1 PAGE 570"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 34,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Indicated power developed = 13.30 kW\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "Pmi=6#.....................#Mean effective pressure in bar\n",
+    "N=1000#....................#Engine rpm\n",
+    "d=0.11#.....................#Diameter of piston in m\n",
+    "l=0.14#.....................#Stroke length in m\n",
+    "n=1#........................#No of cylinders\n",
+    "k=1#........................#k=1 for two stroke engine\n",
+    "#Calculations\n",
+    "V=l*(pi/4)*d*d#.............#Volume of the cylinder in m**3\n",
+    "IP=(n*Pmi*V*k*10*N)/6#.........#Indicated Power developed in kW\n",
+    "print \"Indicated power developed = %0.2f kW\"%IP"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.2 PAGE 571"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 35,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The bore of the engine = 87.96 mm\n",
+      "The stroke of the engine = 131.94 mm\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "n=4#........................#No of cylinders\n",
+    "P=14.7#....................#Power developed in kW\n",
+    "N=1000#....................#Engine speed in rpm\n",
+    "Pmi=5.5#....................#Mean effective pressure in bar\n",
+    "lbyd=1.5#...................#Ratio of stroke to bore\n",
+    "k=0.5#.......................#For four stroke engine\n",
+    "#Calculations\n",
+    "d=((P*6)/(n*Pmi*N*k*10*(pi/4)*lbyd))**(1/3)#......................#Calculation of bore in m\n",
+    "l=lbyd*d#................................#Calculation of stroke in m\n",
+    "print \"The bore of the engine = %0.2f mm\"%(d*1000)\n",
+    "print \"The stroke of the engine = %0.2f mm\"%(l*1000)\n"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.3 PAGE 572"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 36,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Brake Power = 2.51 KW\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "Db=0.6#.....................#Diameter of the brake wheel in m\n",
+    "d=0.026#......................#Diameter of the rope in m\n",
+    "W=200#.......................#Dead load on the brake in N\n",
+    "S=30#......................#Spring balance reading in N\n",
+    "N=450#......................#Engine speed in rpm\n",
+    "#Calculations\n",
+    "BP=((W-S)*pi*(Db+d)*N)/(60*1000)#...............#Brake Power in KW\n",
+    "print \"Brake Power = %0.2f KW\"%(BP)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.4 PAGE 572"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 37,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Since it is given that the stroke is equal to bore, their value is = 138.67 mm\n",
+      "The engine displacement = 0.00 m**3\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "n=4#........................#No of cylinders\n",
+    "k=0.5#......................#For four stroke engine\n",
+    "Tb=160#.....................#Max brake torque in Nm\n",
+    "N=3000#......................#Engine rpm\n",
+    "Pm=9.6#....................#Brake mean effective pressure in bar\n",
+    "#Calculations\n",
+    "D=((2*pi*N*Tb*6)/(60*1000*Pm*(pi/4)*N*k*10))**(1/3)#.....................#Bore of engine in m\n",
+    "L=D#...................#Given that the stroke is equal to bore\n",
+    "Disp=(pi/4)*D*D*L#....................................#Displacement in m**3\n",
+    "print \"Since it is given that the stroke is equal to bore, their value is = %0.2f mm\"%(D*1000)\n",
+    "print \"The engine displacement = %0.2f m**3\"%(Disp)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.5 PAGE 572"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 38,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Since the stroke and bore are equal, their value is = 290.90 mm\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "n=6#.....................#No of cylinders\n",
+    "Pmb=6#....................#Brake mean effective pressure in bar\n",
+    "N=1000#..................#Engine rpm\n",
+    "k=0.5#.......................#For four stroke engine\n",
+    "Wce=820#.................#Work during compression and expansion in kW\n",
+    "Wie=50#...................#Work during intake and exhaust in kW\n",
+    "f=150#......................#Rubbing friction in engiine in kW\n",
+    "WnetT=40#...................#Net work done by turbine in kW\n",
+    "#Calculations\n",
+    "BP=Wce-(Wie+f+WnetT)#.....................#Net work available or brake power in kW\n",
+    "D=((BP*6)/(n*Pmb*(pi/4)*N*k*10))**(1/3)#......................#Bore of engine in m\n",
+    "L=D#.........................................#Given that bore is equal to stroke\n",
+    "print \"Since the stroke and bore are equal, their value is = %0.2f mm\"%(D*1000)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.6 PAGE 573"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 39,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Ratio of the power input of the engine with methane fuel to that with octane : 1.12\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "Cm=50150#............................#Heating value of methane in kJ/kg\n",
+    "Co=44880#............................#Heating value of octane in kJ/kg\n",
+    "#Calculations\n",
+    "#Since Energy supplied is proportional to mass of fuel supplied time calorific value of the fuel supplied\n",
+    "ratioP=Cm/Co#.........................#Ratio of the power input of the engine with methane fuel to that with octane\n",
+    "print \"Ratio of the power input of the engine with methane fuel to that with octane : %0.2f\"%ratioP"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.7 PAGE 573"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 40,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The Brake power = 250.00 kW\n",
+      "Brake thermal efficiency = 33.07 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "N=2000#...........................#Engine rpm\n",
+    "k=0.5#..............................#Four stroke engine\n",
+    "Disp=0.025#........................#Engine displacement in m**3\n",
+    "Pmb=6#..............................#Brake mean effective pressure in bar\n",
+    "mf=0.018#............................#Fuel consumption in kg/s\n",
+    "Cf=42000#............................#Calorific value of fuel in kJ/kg\n",
+    "#Calcuations \n",
+    "BP=(Pmb*Disp*N*k*10)/(6)#................#Brake power in kW\n",
+    "etaBT=BP/(mf*Cf)#.................#Brake thermal efficiency\n",
+    "print \"The Brake power = %0.2f kW\"%(BP)\n",
+    "print \"Brake thermal efficiency = %0.2f %%\"%(etaBT*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.8 PAGE 574"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 41,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Brake power developed by engine = 9.16 kW\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "T=175#.......................#Torque due to brake load in Nm\n",
+    "N=500#.........................#Engine speed in rpm\n",
+    "#calcuations\n",
+    "BP=(2*pi*N*T)/(60*1000)#.......................#Brake power developed by engine in kW\n",
+    "print \"Brake power developed by engine = %0.2f kW\"%(BP)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.9 PAGE 575"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 42,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Indicated power = 47.71 kW\n",
+      "Brake power = 42.88 kW\n",
+      "Mechanical efficiency = 89.88 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "D=0.3#.............................#Bore of engine cylinder in m\n",
+    "L=0.45#............................#Stroke of engine cylinder in m\n",
+    "N=300#.............................#Engine rpm\n",
+    "Pmi=6#.............................#Indicated mean effective pressure in bar\n",
+    "Nbl=1.5#...........................#Net brake load in kN\n",
+    "Db=1.8#............................#Diameter of brake drum in m\n",
+    "d=0.02#............................#Brake rope diameter\n",
+    "k=0.5#.............................#Four stroke engine\n",
+    "n=1#...............................#No of cylinders\n",
+    "#Calculations\n",
+    "IP=(n*Pmi*L*(pi/4)*D*D*N*k*10)/6#......................#Indicated power in kW\n",
+    "BP=(Nbl*pi*(Db+d)*N)/60#...............................#Brake power in kW\n",
+    "etam=BP/IP#.............................................#Mechanical efficiency\n",
+    "print \"Indicated power = %0.2f kW\"%(IP)\n",
+    "print \"Brake power = %0.2f kW\"%(BP)\n",
+    "print \"Mechanical efficiency = %0.2f %%\"%(etam*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.10 PAGE 576"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 43,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Brake specific fuel consumption = 0.27 kJ/hW-h\n",
+      "Brake thermal efficiency : 30.78 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "Db=0.7#.............................#Diameter of brake pulley in m\n",
+    "d=0.025#............................#Diameter of the rope in m\n",
+    "W=50#...............................#Load on the tight side of the rope in kg\n",
+    "S=50#...............................#Spring balance reading in N\n",
+    "N=900#..............................#Engine rpm\n",
+    "mf=4#...............................#Rate of fuel consumption in kg/h\n",
+    "C=44000#............................#Calorific value of fuel in kJ/kg\n",
+    "g=9.81#.............................#Acceleration due to gravity in m/s**2\n",
+    "#Calculations\n",
+    "BP=(((W*g)-S)*pi*(Db+d)*N)/(60*1000)#........................#Brake power in kW\n",
+    "bsfc=mf/BP#...................................................#Brake specific fuel consumption in kJ/hW-h\n",
+    "print \"Brake specific fuel consumption = %0.2f kJ/hW-h\"%bsfc\n",
+    "etathB=(BP*3600)/(mf*C)#.............................................#Brake thermal efficiency\n",
+    "print \"Brake thermal efficiency : %0.2f %%\"%(etathB*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.11 PAGE 576"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 44,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Indicated thermal efficiency = 42.52 %\n",
+      "Brake power = 100.53 kW\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "n=4#.......................#No of cylinders\n",
+    "k=0.5#.....................#Four stroke engine\n",
+    "r=8#.......................#Compression ratio\n",
+    "d=0.1#.....................#Engine bore in m\n",
+    "l=0.1#.....................#Engine stroke in m\n",
+    "etaV=0.75#.................#Volumetric efficiency\n",
+    "N=4800#....................#Engine rpm\n",
+    "afr=15#....................#Air fuel ratio\n",
+    "C=42000000#................#Calorific value of fuel\n",
+    "rhoa=1.12#.................#Atmospheric density in kg/m**3\n",
+    "Pmi=10#....................#Mean effective pressure in bar\n",
+    "etamech=0.8#...............#Mechanical efficiency\n",
+    "#Calculations \n",
+    "IP=(n*Pmi*l*(pi/4)*d*d*N*k*10)/6#.................#Indicated power in kW\n",
+    "Ac=n*(pi/4)*d*d*l*(N/2)*(etaV/60)#.....................#Air consumption in m**3/s\n",
+    "ma=Ac*rhoa#........................................#Mass flow of air in kg/s\n",
+    "mf=ma/afr#.........................................#Mass flow of fuel in kg/s\n",
+    "etath=(IP*1000)/(mf*C)#...................................#Indicated thermal efficiency\n",
+    "print \"Indicated thermal efficiency = %0.2f %%\"%(etath*100)\n",
+    "BP=IP*etamech#.....................................#Brake Power in kW\n",
+    "print \"Brake power = %0.2f kW\"%BP"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 7.12 PAGE 577"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 45,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The volumetric efficiency = 84.48 %\n",
+      "Brake specific fuel consumption = 0.28 kg/kWh\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "N=1800#...................#Engine rpm\n",
+    "l=0.11#...................#Engine stroke in m\n",
+    "d=0.085#..................#Engine bore in m\n",
+    "ma=0.56#..................#Air flow rate in kg/min\n",
+    "BP=6#.....................#Brake power developed in kW\n",
+    "afr=20#...................#Air fuel ratio\n",
+    "C=42550#..................#Calorific value of fuel in kJ/kg\n",
+    "rhof=1.18#................#Density of fuel in kg/m**3\n",
+    "#calculations\n",
+    "V=(pi/4)*d*d*l*(N/2)#.....................#Volume displacemt in m**3/min\n",
+    "Ma=V*rhof#.................................#Mass of air in kg/min\n",
+    "etaV=ma/Ma#................................#Volumetric efficiency\n",
+    "fc=ma/afr#.................................#Fuel concumption\n",
+    "bsfc=(fc*60)/BP#...........................#Brake specific fuel consumption in kg/kWh\n",
+    "print \"The volumetric efficiency = %0.2f %%\"%(etaV*100)\n",
+    "print \"Brake specific fuel consumption = %0.2f kg/kWh\"%(bsfc)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.13 PAGE 578"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 46,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The mechanical efficiency = 63.59 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "pmicover=6.5#....................#Mean effective pressure on cover side in bar\n",
+    "pmicrank=7#......................#Mean effective pressure on crank side in bar\n",
+    "D=0.2#...........................#Engine bore in m\n",
+    "l=0.35#..........................#Engine stroke in m\n",
+    "drod=0.02#.........................#Diameter of piston rod in m\n",
+    "W=1370#............................#Dead load on the brake in N\n",
+    "S=145#.............................#Spring balance reading in N\n",
+    "Db=1.2#............................#Brake wheel diameter in m\n",
+    "d=0.02#............................#Brake rope diameter in m\n",
+    "k=0.5#.............................#Four stroke engine\n",
+    "N=420#.......................#Engine rpm\n",
+    "#calculations\n",
+    "Acover=(pi/4)*D*D#.......................#Area of cylinder on the cover side in m**2\n",
+    "Acrank=(pi/4)*((D**2)-(drod**2))#..........#Effective area of cylinder on the crank end side in m**2\n",
+    "IPcover=(pmicover*l*Acover*N*k*10)/6#................#Indicated power on the cover end side in kW\n",
+    "IPcrank=(pmicrank*l*Acrank*N*k*10)/6#................#Indicated power on the crank end side in kW\n",
+    "IPtotal=IPcover+IPcrank#....................#TOtal\n",
+    "BP=((W-S)*pi*(Db+d)*N)/(60*1000)#...................#Brake power in kW\n",
+    "etamech=BP/IPtotal#..................................#Mechanical efficiency\n",
+    "print \"The mechanical efficiency = %0.2f %%\"%(etamech*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.14 PAGE 579"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 47,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Engine bore = 152.98 mm\n",
+      "Engine stroke = 229.47 mm\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "BP=14.7#........................#Brake power in kW\n",
+    "p1=0.9#.........................#Suction pressure in bar\n",
+    "etamech=0.8#....................#Mechanical efficiency\n",
+    "r=5#............................#Compression ratio\n",
+    "p3=24#..........................#maximum explosion pressure in bar\n",
+    "N=1000#.........................#Engine rpm\n",
+    "rld=1.5#........................#Ratio of length and stroke\n",
+    "ic=1.35#........................#Index of compression curve\n",
+    "ie=1.3#.........................#Index of expansion curve\n",
+    "k=0.5#..........................#Four stroke engine\n",
+    "#calculations\n",
+    "p2=(r**ic)*p1#......................#intermediate pressure = %0.2f bar) during compression\n",
+    "p4=p3/(r**ie)#......................#Intermediate pressure = %0.2f bar) during expansion\n",
+    "pm=((((p3-r*p4)/(ie-1))-((p2-p1*r)/(ic-1)))*(10**5))/(r-1)#...........#Mean effective pressure in N/m**2\n",
+    "pmb=pm/100000#........................................#Mean effective pressure in bar\n",
+    "IP=BP/etamech#........................................#Indicated power in kW\n",
+    "D=((IP*6*4)/(pmb*rld*(pi)*N*k*10))**(1/3)#............#Engine bore in m\n",
+    "L=rld*D#..............................................#Engine stroke in m\n",
+    "print \"Engine bore = %0.2f mm\"%(D*1000)\n",
+    "print \"Engine stroke = %0.2f mm\"%(L*1000)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.15 PAGE 580"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 48,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Indicated thermal efficiency = 27.03 %\n",
+      "Indicated brake efficiency = 23.43 %\n",
+      "Mechanical efficiency = 86.67 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "#Initialisation of Variables\n",
+    "IP=30#........................#Indicated power in kW\n",
+    "BP=26#........................#Brake power in kW\n",
+    "N=1000#.......................#Engine rpm\n",
+    "fpbph=0.35#...................#Fuel per brake power hour in kg/B.P.h\n",
+    "C=43900#......................#Calorific value of fuel used in kJ/kg\n",
+    "#Calculations\n",
+    "mf=BP*fpbph#.............#Fuel consumption per hour in kg/h\n",
+    "etaIth=IP/((mf/3600)*C)#.................#Indicated thermal efficiency\n",
+    "etaBth=BP/((mf/3600)*C)#.................#Indicated brake efficiency\n",
+    "etamech=BP/IP#...........................#Mechanical efficiency\n",
+    "print \"Indicated thermal efficiency = %0.2f %%\"%(etaIth*100)\n",
+    "print \"Indicated brake efficiency = %0.2f %%\"%(etaBth*100)\n",
+    "print \"Mechanical efficiency = %0.2f %%\"%(etamech*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.16 PAGE 581"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 49,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Brake specific fuel consumption  = 0.29 kg/kWh\n",
+      "Brake thermal efficiency = 28.62 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "#Initialisation of Variables\n",
+    "Db=0.75#.....................#Diameter of brake pulley in m\n",
+    "d=0.05#......................#Rope diameter in m\n",
+    "W=400#.......................#Dead load in N\n",
+    "S=50#........................#Spring balance reading in N\n",
+    "cf=4.2#......................#Consumption of fuel in kg/h\n",
+    "N=1000#......................#Engine rpm\n",
+    "C=43900#.....................#Calorific value of fuel in kJ/kg\n",
+    "#Calculations\n",
+    "BP=((W-S)*pi*(Db+d)*N)/(60*1000)#...............#Brake power in kW\n",
+    "bsfc=cf/BP#......................................#Brake specific fuel consumption  in kg/kWh\n",
+    "etabth=BP/((cf/3600)*C)#.........................#Brake thermal efficiency\n",
+    "print \"Brake specific fuel consumption  = %0.2f kg/kWh\"%(bsfc)\n",
+    "print \"Brake thermal efficiency = %0.2f %%\"%(etabth*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.17 PAGE 581"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 50,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The calorific value of the fuel used = 40341.03 kJ/kg\n",
+      "Fuel consumption = 20.52 (kg/h\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "#Initialisation of Variables\n",
+    "n=6#.............................#No of cylinders\n",
+    "D=0.09#..........................#Bore of cylinder in m\n",
+    "L=0.1#...........................#Stroke length in m\n",
+    "r=7#.............................#Compression ratio\n",
+    "etarel=0.55#.....................#Relative efficiency\n",
+    "isfc=0.3#........................#Indicated specific fuel consumption in kg/kWh\n",
+    "imep=8.6#........................#Indicated mean effective pressure in bar\n",
+    "N=2500#..........................#Engine speed\n",
+    "ga=1.4#..........................#Degree of freedom for air\n",
+    "k=0.5#...........................#Four stroke engine\n",
+    "#calculations\n",
+    "etastan=1-1/(r**(ga-1))#...................#Air standard efficiency\n",
+    "etath=etarel*etastan#.....................#Indicated thermal efficiency \n",
+    "C=3600/(etath*isfc)#.......................#Calorific value of fuel in kJ/kg\n",
+    "IP=(n*imep*L*D*D*(pi/4)*N*k*10)/6#................#Indicated power in kW\n",
+    "fc=IP*isfc#.............................#Fuel consumption in kg/h\n",
+    "print \"The calorific value of the fuel used = %0.2f kJ/kg\"%(C)\n",
+    "print \"Fuel consumption = %0.2f (kg/h\"%(fc)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.18 PAGE 582"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 51,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Engine bore = 62.04 mm\n",
+      "Engine stroke = 93.05 mm\n",
+      "Fuel consumption = 8.79 kg/h\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "BP=30#........................#Brake power in kW\n",
+    "pmi=8#.........................#Mean effective pressure in bar\n",
+    "etamech=0.8#....................#Mechanical efficiency\n",
+    "n=4#............................#No of cylinders\n",
+    "N=2500#.........................#Engine rpm\n",
+    "rld=1.5#........................#Ratio of length and stroke\n",
+    "etabth=0.28#......................#Brake thermal efficiency\n",
+    "k=1#..........................#Two stroke engine\n",
+    "C=43900#.........................#Calorific value of fuel in kJ/kg\n",
+    "#calculations\n",
+    "IP=BP/etamech#........................................#Indicated power in kW\n",
+    "D=((IP*6*4)/(pmi*n*rld*(pi)*N*k*10))**(1/3)#............#Engine bore in m\n",
+    "L=rld*D#..............................................#Engine stroke in m\n",
+    "print \"Engine bore = %0.2f mm\"%(D*1000)\n",
+    "print \"Engine stroke = %0.2f mm\"%(L*1000)\n",
+    "mf=BP/(etabth*C)#..............................#Fuel consumption in kg/s\n",
+    "print \"Fuel consumption = %0.2f kg/h\"%(mf*3600)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.19 PAGE 583"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 52,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The volumetric efficiency of the engine = 78.16 %\n",
+      "The brake thermal efficiency of the engine = 23.64 %\n",
+      "Brake torque = 0.23 kNm\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "n=6#......................#No of cylinders\n",
+    "pdpc=700*10**(-6)#.................#Piston displacement per cylinder in m**3\n",
+    "P=78#............................#Power developed in kW\n",
+    "N=3200#.............................#Engine rpm\n",
+    "mf=27#.............................#Fuel consumption in kg/h\n",
+    "C=44000#...........................#Calorific value of fuel in kJ/kg\n",
+    "afr=12#..............................#Air fuel ratio\n",
+    "p1=0.9#..........................#Intake air pressure\n",
+    "pa=p1#\n",
+    "t1=305#...............................#Intake air temperature\n",
+    "ta=t1#\n",
+    "R=0.287#.....................#Gas constant in kJ/kgK\n",
+    "#Calculations\n",
+    "ma=afr*mf#............................#maaa of air in kg/h\n",
+    "Va=(ma*R*t1)/(p1*100)#.............#Volume of air intake in m**3/h\n",
+    "Vs=pdpc*n*(N/2)*60#.....................#Swept volume in m**3/h\n",
+    "etaV=Va/Vs#.............................#Volumetric efficiency\n",
+    "print \"The volumetric efficiency of the engine = %0.2f %%\"%(etaV*100)\n",
+    "etabt=P/(mf*(C/3600))#...................#Brake thermal efficiency\n",
+    "print \"The brake thermal efficiency of the engine = %0.2f %%\"%(etabt*100)\n",
+    "Tb=(P*60)/(2*pi*N)#..........................#Brake torque in kNm\n",
+    "print \"Brake torque = %0.2f kNm\"%(Tb)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.20 PAGE 583"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 53,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Average no of times each cylinder misfires in one min : 2.00\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi,floor\n",
+    "# Initialisation of Variables\n",
+    "n=6#.......................#No of cylinders\n",
+    "Vs=1.75*10**(-3)#..............#Stroke volume in m**3\n",
+    "IP=26.3#.....................#Indicated power in kW\n",
+    "Ne=504#.......................#Expected Engine rpm\n",
+    "Pmi=6#........................#Mean effective pressure in bar\n",
+    "k=0.5#.........................#Four stroke engine\n",
+    "#Calculations\n",
+    "Na=floor((IP*6)/(n*Pmi*Vs*k*10))#.......................#Actual Engine rpm\n",
+    "af=(Na*n)/2#.......................#Actual no of fires in min\n",
+    "ef=(Ne*n)/2#.......................#Expected no of fires in min\n",
+    "Nm=ef-af#........................#No of misfires/min\n",
+    "nm=Nm/n#....................#Average no of times each cylinder misfires in one min\n",
+    "print \"Average no of times each cylinder misfires in one min : %0.2f\"%nm"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.21 PAGE 584"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 1,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Indicated power = 14.24 kW\n",
+      "Indicated thermal efficiency = 34.63 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "n=4#.......................#No of cylinders\n",
+    "D=0.075#.......................#Engine bore in m\n",
+    "L=0.09#........................#Engine length in m\n",
+    "err=39/8#.......................#Engine to rear axle ratio\n",
+    "Dw=0.65#.........................#Wheel diameter in m\n",
+    "pc=0.227#.......................#Petrol consumption in kg\n",
+    "pmi=5.625#.........................#Mean effective pressure in bar\n",
+    "C=43470#..............................#Calorific value of petrol in kJ/kg\n",
+    "k=0.5#.............................#Four stroke engine\n",
+    "sc=48#............................#Speed of the car in km/h\n",
+    "d=3.2#.............................#Distance covered by car in km\n",
+    "#Calculations\n",
+    "sc1=sc*(1000/60)#...................#Speed of the car in m/min\n",
+    "Nt=sc1/(pi*Dw)#......................#Revolutions made by tire per min\n",
+    "Ne=Nt*err#............................#Speed of engine shaft\n",
+    "IP=(n*pmi*L*(pi/4)*D*D*Ne*k*10)/6#........#Indicated power in kW\n",
+    "print \"Indicated power = %0.2f kW\"%(IP)\n",
+    "sc2=sc/60#.......................#Speed of the car in km/min\n",
+    "t=d/sc2#..........................#Time for covering 3.2 km in min\n",
+    "fc=pc/(t*60)#.....................#Fuel consumed per second in kg\n",
+    "etait=IP/(fc*C)#...............#Indicated thermal efficiency\n",
+    "print \"Indicated thermal efficiency = %0.2f %%\"%(etait*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.22 PAGE 584"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 2,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Indicated power = 26.59 kW\n",
+      "Brake power = 21.21 kW\n",
+      "Mechanical efficiency = 79.75 %\n",
+      "Indicated thermal efficiency = 21.61 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "n=1#.................#No of cylinders\n",
+    "D=0.25#................#Engine bore in m\n",
+    "L=0.4#.................#Engine stroke in m\n",
+    "pmg=7#.................#Gross mean effective pressure in bar\n",
+    "pmp=0.5#...............#Pumping mean effective pressure in bar\n",
+    "N=250#..................#Engine rpm\n",
+    "Db=1.5#................#Effective diameter of the brake in m\n",
+    "Nl=1080#..............#Net load on the brake in N\n",
+    "fh=10#.................#Fuel used per hour in kg\n",
+    "C=44300#...............#Calorific value of fuel in kJ/kg\n",
+    "k=0.5#.................#Four stroke engine\n",
+    "#Calculations\n",
+    "mf=fh/3600#.........................#Fuel used per second in kg\n",
+    "pm=pmg-pmp#.......................#Net pressure\n",
+    "IP=(n*pm*L*(pi/4)*D*D*N*k*10)/6#..........#/Indicated power in kW\n",
+    "print \"Indicated power = %0.2f kW\"%(IP)\n",
+    "BP=((Nl)*pi*Db*N)/(60*1000)#...............#Brake power in kW\n",
+    "print \"Brake power = %0.2f kW\"%(BP)\n",
+    "etamech=BP/IP#...........................#Mechanical efficiency\n",
+    "print \"Mechanical efficiency = %0.2f %%\"%(etamech*100)\n",
+    "etath=IP/(mf*C)#.........................#Indicated thermal efficiency\n",
+    "print \"Indicated thermal efficiency = %0.2f %%\"%(etath*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.23 PAGE 585"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 3,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Brake mean effective pressure = 553.38 bar\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "etabth=0.3#....................#Brake thermal efficiency\n",
+    "afrw=20#........................#Air fuel ratio by weight\n",
+    "C=41800#.........................#Calorific value of fuel used in kJ/kg\n",
+    "R=287#........................#Gas constant in J/kg\n",
+    "#Calculations\n",
+    "Wp=etabth*C#...................#Work produced per kg of fuel in kJ\n",
+    "p1=1.0132#t=273+15#............#STP conditions in bar and Kelvin\n",
+    "V=(afrw*t*R)/(p1*10**5)#.......#Volume of air used in m**3\n",
+    "pmb=(Wp*1000)/(V*10**5)#........#Brake mean effective pressure in bar\n",
+    "print \"Brake mean effective pressure = %0.2f bar\"%(pmb)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.24 PAGE 585"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 4,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Volumetric efficiency = 85.67 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "v1=0.216#.....................#Gas consumption in m**3/min\n",
+    "pw=75#........................#Pressure of gas in mm of water\n",
+    "t1=290#......................#Temperature of gas in K\n",
+    "ac=2.84#....................#Air consumption in kg/min\n",
+    "br=745#......................#Barometer reading in m of Hg\n",
+    "D=0.25#.....................#Engine bore in m\n",
+    "L=0.475#......................#Engine stroke in m\n",
+    "N=240#........................#Engine rpm\n",
+    "R=287#......................#Gas constant for air in J/kgK\n",
+    "#Calculations\n",
+    "p1=br+(pw/13.6)#...................#Pressure of gas in mm of mercury\n",
+    "p2=760\n",
+    "t2=273#.....................#NTP conditions in mm of Hg and Kelvin\n",
+    "v2=(p1*v1*t2)/(t1*p2)#...............#Volume of gas used at NTP in m**3\n",
+    "gs=v2/(N/2)#.........................#Gas used per stroke in m**3\n",
+    "v=(ac*R*t2)/(1.0132*10**5)#...........#Volume occupied by air at NTP in m**3/min\n",
+    "aps=v/(N/2)#...........................#Air used per stroke\n",
+    "Va=gs+aps#.....................#Actual volume of mixture in m**3 drawn per stroke at NTP\n",
+    "Vs=(pi/4)*D*D*L#...............#Swept volume in mm**3\n",
+    "etaV=(Va/Vs)#...................#Volumetric efficiency\n",
+    "print \"Volumetric efficiency = %0.2f %%\"%(etaV*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.25 PAGE 586"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 5,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Indicated power = 26.59 kW\n",
+      "Brake power = 22.87 kW\n",
+      "Mechanical efficiency = 86.00 %\n",
+      "Indicated thermal efficiency = 22.79 %\n",
+      "Relative efficiency = 43.24 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "t=1#...................#Duration of trial in hrs\n",
+    "Rev=14000#.............#Revolutions\n",
+    "nmc=500#...............#Number of missed cycles\n",
+    "bl=1470#................#Net Brake load in N\n",
+    "mep=7.5#................#Mean effective pressure in bar\n",
+    "gc=20000#...............#Gas consumption in litres\n",
+    "lcv=21#.................#LCV of gas at supply condition in kJ/litre\n",
+    "D=0.25#.................#Engine bore in m\n",
+    "L=0.4#.................#Engine stroke in m\n",
+    "r=6.5#..................#Compression ratio\n",
+    "n=1#......................#No of cylinders\n",
+    "Cb=4#......................#Effective brake Circumference \n",
+    "k=0.5#....................#Four stroke engine\n",
+    "ga=1.4#......................#Degree of freedom\n",
+    "#Calculations\n",
+    "N=Rev/60#..............#Engine rpm\n",
+    "Vg=gc/3600#.............#Fuel consumption in litres/s\n",
+    "Na=((Rev/2)-nmc)/60#................#Working cycles per min\n",
+    "IP=(n*mep*L*(pi/4)*D*D*Na*10)/6#............#indicated power in kW\n",
+    "print \"Indicated power = %0.2f kW\"%(IP)\n",
+    "BP=((bl)*Cb*N)/(60*1000)#...............#Brake power in kW\n",
+    "print \"Brake power = %0.2f kW\"%(BP)\n",
+    "etamech=BP/IP#...........................#Mechanical efficiency\n",
+    "print \"Mechanical efficiency = %0.2f %%\"%(etamech*100)\n",
+    "etath=IP/(Vg*lcv)#.........................#Indicated thermal efficiency\n",
+    "print \"Indicated thermal efficiency = %0.2f %%\"%(etath*100)\n",
+    "etast=1-(1/r**(ga-1))#............#Air standard efficiency \n",
+    "etarel=etath/etast#............#Relative efficiency\n",
+    "print \"Relative efficiency = %0.2f %%\"%(etarel*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.26 PAGE 587"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 6,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The compression ratio : 5.58\n",
+      "Thermal efficiency = 19.89 %\n",
+      "Gas consumption = 0.96 m**3/IP hour\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "n=1.3#...................#Index of compression\n",
+    "pa=1.4#\n",
+    "pb=3.6#\n",
+    "posa=(1/4)#..........#Point a - the position 1/4 of the stroke\n",
+    "posb=(3/4)#..........#Point b - the position 3/4 of the stroke\n",
+    "ga=1.4#...............#Degree of freedom for gas\n",
+    "etarel=0.4#...................#Relative efficiency\n",
+    "C=18800#....................#Calorific value of fuel in kJ/m**3\n",
+    "#Calculations\n",
+    "r=1+((((pb/pa)**(1/n))-1)/(posb-(((pb/pa)**(1/n))*(posa))))#.........#Compression ratio\n",
+    "print \"The compression ratio : %0.2f\"%r\n",
+    "etast=1-(1/r**(ga-1))#............#Air standard efficiency \n",
+    "etath=etarel*etast#............#Thermal efficiency\n",
+    "print \"Thermal efficiency = %0.2f %%\"%(etath*100)\n",
+    "v=1/(etath*C)#...............#Gas consumption per IP sec\n",
+    "print \"Gas consumption = %0.2f m**3/IP hour\"%(v*3600)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.27 PAGE 587"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 7,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Mean effective pressure developed = 6.54 bar\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "n=6#.....................#No of cylinders\n",
+    "r=5#..................#Compression ratio\n",
+    "Vc=0.000115#................#Clearance volume of each cylinder in m**3\n",
+    "fc=10.5#.....................#Fuel consumed in kg/h\n",
+    "C=41800#......................#Calorific value of fuel in  kJ/kg\n",
+    "N=2500#.......................#Engine speed in rpm\n",
+    "er=0.65#.......................#Efficiency ratio\n",
+    "ga=1.4#........................#Degree of freedom\n",
+    "#calculations\n",
+    "etast=1-(1/r**(ga-1))#...............................#Air standard efficiency\n",
+    "etath=etast*er#.................................#Thermal efficiency\n",
+    "IP=etath*(fc/3600)*C#..........................#Indicated power in kW\n",
+    "Wnet=(IP*(10**3)*60)/(n*(N/2))#..............#Net work froom one cycle per cylinder in N-m\n",
+    "Vs=(r-1)*Vc#......................#Swept volume in m**3\n",
+    "pm=Wnet/(Vs*10**5)#...................#Mean effective pressure developed\n",
+    "print \"Mean effective pressure developed = %0.2f bar\"%(pm)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.28 PAGE 588"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 8,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Mean effective pressure = 8.11 bar\n",
+      "Brake mean effective pressure = 6.16 bar\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "D=0.2#.................#Engine bore in m\n",
+    "L=0.25#...............#Engine stroke in m\n",
+    "n=2#......................#No of cylinders\n",
+    "r=13#......................#Compression ratio\n",
+    "fc=14#..................#Fuel consumption in kg/h\n",
+    "N=300#....................#Engine rpm\n",
+    "etarel=0.65#..............#Relative efficiency\n",
+    "etamech=0.76#.............#Mechanical efficiency\n",
+    "co=0.05#.....................#Cut off of the stroke\n",
+    "C=41800#.....................#Calorific value of fuel in kJ/kg\n",
+    "k=1#........................#Two stroke engine\n",
+    "ga=1.4#.......................#Degree of freedom\n",
+    "#calculations\n",
+    "rho=1+(co*(r-1))#\n",
+    "etast=1-((1/(r**(ga-1)))*(1/ga)*((rho**ga)-1)*(1/(rho-1)))#............#Air standard efficiency\n",
+    "etath=etarel*etast#........................#Thermal efficiency\n",
+    "IP=etath*(fc/3600)*C#........................#Indicated power in kW\n",
+    "BP=etamech*IP#................................#Brake power in kW\n",
+    "pmi=(6*IP)/(n*N*L*(pi/4)*D*D*k*10)#............#mean effective pressure in bar\n",
+    "print \"Mean effective pressure = %0.2f bar\"%(pmi)\n",
+    "pmb=pmi*etamech#...........................#Brake mean effective pressure in bar\n",
+    "print \"Brake mean effective pressure = %0.2f bar\"%(pmb)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.29 PAGE 589"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 9,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The compression ratio : 6.26\n",
+      "Indicated thermal efficiency : 36.40 %\n",
+      "Brake specific fuel consumption = 0.27 kg/kWs\n",
+      "Engine bore = 108.20 mm\n",
+      "Engine stroke = 135.25 mm\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "n=4#.................#No of cylinders\n",
+    "C=45200#..................#calorific value of fuel in kJ/kg\n",
+    "etamech=0.82#...............#Mechanical efficiency\n",
+    "etarel=0.7#.................#Relative efficiency\n",
+    "etast=0.52#...............#Air standard efficiency\n",
+    "etav=0.78#...............#Volumetric efficiency\n",
+    "sbr=1.25#...................#Stroke bore ratio\n",
+    "N=2400#...................#Engine rpm\n",
+    "p=1#.......................#Suction pressure in bar\n",
+    "t=298#....................#Suction temperature in bar\n",
+    "BP=72#...................#Brake power in kW\n",
+    "ga=1.4#......................#Degree of freedom\n",
+    "afr=16#.................#Air fuel ratio\n",
+    "R=287#.......................#Gas constant in J/kg\n",
+    "#calculations\n",
+    "r=(1/(1-etast))**(1/(ga-1))#............#Compression ratio\n",
+    "print \"The compression ratio : %0.2f\"%r\n",
+    "etath=etast*etarel#......................#Indicated thermal efficiency\n",
+    "print \"Indicated thermal efficiency : %0.2f %%\"%(etath*100)\n",
+    "IP=BP/etamech#....................#Indicated power in kW\n",
+    "mf=IP/(etath*C)#......................#Fuel consumption in kg/s\n",
+    "bsfc=mf/BP#......................#Brake specific fuel consumption in kg/kWs\n",
+    "print \"Brake specific fuel consumption = %0.2f kg/kWs\"%(bsfc*3600)\n",
+    "mafm=afr+1#......................#Mass of air fuel mixture in kg/kg of fuel\n",
+    "mafm1=mafm*mf#....................#Mass of air fuel mixture when mf amount of fuel is supplied to engine per second\n",
+    "v=(mafm1*R*t)/(p*10**5)#.......................#/Volume of air fuel mixture supplied to the engine in m**3\n",
+    "Vs=v/etav#..............................#Swept volume in m**3\n",
+    "D=((Vs)/((pi/4)*sbr*n*(N/(2*60))))**(1/3)#............#Engine bore in m\n",
+    "print \"Engine bore = %0.2f mm\"%(D*1000)\n",
+    "print \"Engine stroke = %0.2f mm\"%(D*1000*sbr)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.30 PAGE 589"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 10,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Brake power = 14.81 kW\n",
+      "Mechanical efficiency = 85.00 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "n=1#.......................#No of cylinders\n",
+    "D=0.18#...................#Engine bore in m\n",
+    "L=0.34#....................#Engine stroke in m\n",
+    "N=400#......................#Engine rpm\n",
+    "mepw=6.4#.................#Mean effective pressure of working loop in bar\n",
+    "mepp=0.36#..................#Mean effective pressure of pumping loop in bar\n",
+    "mepd=0.64#.................#Mean effective pressure (dead cycle) iin bar\n",
+    "fs=46#................#Firing strokes per min\n",
+    "#calculations\n",
+    "pminet=mepw-mepp#..........#Net indicated mean effective pressure in bar\n",
+    "dc=(N/2)-fs#...............#Dead cycles per min\n",
+    "IPnet=(n*pminet*(pi/4)*L*D*D*fs*4*10)/6#.............#Net indicated power output in kW\n",
+    "ppdc=(n*pminet*L*(pi/4)*D*D*10*dc)/6#.............#Pumping power of dead cycles in kW\n",
+    "FP=IPnet-ppdc#...........................#Frictional power in kW\n",
+    "IP=(n*pminet*L*(pi/4)*D*D*(N/2)*10)/6#...............#Indicated power in kW\n",
+    "BP=IP-FP#..................#Brake power in kW\n",
+    "print \"Brake power = %0.2f kW\"%(BP)\n",
+    "etamech=BP/IP#.................#Mechanical efficiency\n",
+    "print \"Mechanical efficiency = %0.2f %%\"%(etamech*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.31 PAGE 590"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 11,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Mechanical efficiency = 81.61 %\n",
+      "Brake thermal efficiency = 39.54 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "n=1#..............#No of cylinders\n",
+    "B=0.32#...............#Engine bore in m\n",
+    "L=0.42#..............#Engine stroke in m\n",
+    "N=200#................#Engine rpm\n",
+    "Nk=90#..................#No of explosions per min\n",
+    "v1=11.68#............#Gas used in m**3/h\n",
+    "pg=170#................#Pressure of gas in mm of water \n",
+    "br=755#................#Barometer reading in mm of Hg\n",
+    "pmi=6.2#.................#Mean effective pressure in bar\n",
+    "C=21600#.......................#Calorific value of gas in kJ/kg\n",
+    "bl=2040#......................#Net load on brake in N\n",
+    "Db=1.2#......................#Brake drum diameter in m\n",
+    "t1=298#.....................#Ambient temperature in Kelvin\n",
+    "#Calculations\n",
+    "IP=(n*pmi*L*(pi/4)*B*B*Nk*10)/6#..........................#Indicated power in kW\n",
+    "BP=(bl*pi*Db*N)/(60*1000)#.........................#Brake power in kW\n",
+    "etamech=(BP/IP)#...................#Mechanical efficiency\n",
+    "print \"Mechanical efficiency = %0.2f %%\"%(etamech*100)\n",
+    "p1=br+(pg/13.6)#.................#In mm of Hg\n",
+    "p2=760#t2=273#...................#NTP conditions in mm of Hg and Kelvin\n",
+    "v2=(p1*v1*t2)/(p2*t1)#\n",
+    "etabth=BP/((v2/3600)*C)#..............#Brake thermal efficiency\n",
+    "print \"Brake thermal efficiency = %0.2f %%\"%(etabth*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.32 PAGE 591"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 12,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Volumetric efficiency = 66.45 %\n",
+      "Air fuel ratio : 13.20\n",
+      "Mean effective pressure = 7.55 bar\n",
+      "Relative efficiency = 53.79 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi,sqrt\n",
+    "# Initialisation of Variables\n",
+    "n=1#...................#No of cylinders\n",
+    "d=0.032#................#Diameter of circular orifice in m\n",
+    "Cd=0.62#.............#Co efficient of discharge\n",
+    "hw=150#.................#Pressure across orfice in mm of water\n",
+    "t=20+273#..............#Temperature of air in the room in Kelvin\n",
+    "p=1.0132#.................#Ambient pressure in bar\n",
+    "pd=0.00178#............#Piston displacement in m**3\n",
+    "R=287#....................#Gas constant in J/kg\n",
+    "r=6.5#..................#Compression ratio\n",
+    "fc=0.135#................#Fuel consumption in kg/min\n",
+    "C=43900#.................#Calorific value of fuel in kJ/kg\n",
+    "BP=28#................#Brake power in kW\n",
+    "N=2500#...................#Engine rpm\n",
+    "k=0.5#....................#Four stroke engine\n",
+    "g=9.81#.......................#Acceleration due to gravity in m/s**2\n",
+    "rhow=1000#....................#Density of water in kg/m**3\n",
+    "ga=1.4#........................#Degree of freedom\n",
+    "#calculations\n",
+    "mbyv=(p*10**5)/(R*t)#\n",
+    "pw=(hw/rhow)*rhow#....................#Pressure across orifice in kg/m**2\n",
+    "H=pw/mbyv#........................#Head of air column causing the flow in m\n",
+    "ma=Cd*(pi/4)*d*d*sqrt(2*g*H)#................#Air flow through orifice in m**3/s\n",
+    "maps=(ma*60)/(N/2)#........................#Air consumption per stroke\n",
+    "etav=maps/pd#.................#Volumetric efficiency\n",
+    "print \"Volumetric efficiency = %0.2f %%\"%(etav*100)\n",
+    "ac=ma*60*mbyv#...............#Mass of air drawn into cylinder per min in kg\n",
+    "afr=ac/fc#...................#Air fuel ratio\n",
+    "print \"Air fuel ratio : %0.2f\"%afr\n",
+    "pmb=(6*BP)/(n*pd*N*k*10)#...................#Mean effective pressure in bar\n",
+    "print \"Mean effective pressure = %0.2f bar\"%(pmb)\n",
+    "etast=1-(1/(r**(ga-1)))#...............#Air standard efficiency\n",
+    "etabth=BP/((fc/60)*C)#...............#Brake thermal efficiency\n",
+    "etarel=etabth/etast#.................#Relative efficiency\n",
+    "print \"Relative efficiency = %0.2f %%\"%(etarel*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.33 PAGE 591"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 13,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Indicated power = 7.50 kW\n",
+      "Brake power = 8.04 kW\n",
+      "Brake mean effective pressure = 6.00 bar\n",
+      "Brake specific fuel consumption = 0.35 kg/BP h\n",
+      "Brake thermal efficiency = 24.74 %\n",
+      "Indicated thermal efficiency = 30.92 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "N=400#.................#Engine rpm\n",
+    "n=1#....................#no of cylinders\n",
+    "W=370#.................#Load on the brake in N\n",
+    "S=50#..................#Spring balance readin in N\n",
+    "Db=1.2#.................#Diameter of the brake drum\n",
+    "mf=2.8#.................#Fuel consumption in kg/h\n",
+    "C=41800#..................#Calorific value of fuel in kJ/kg\n",
+    "D=0.16#...................#Engine bore in m\n",
+    "L=0.2#....................#Engine stroke in m\n",
+    "k=0.5#.....................#Four stroke engine\n",
+    "Sc=1#....................#Spring constant in bar/mm\n",
+    "l=40#....................#Length of diagram in mm\n",
+    "aic=300#.................#Area of indicator card in mm**2\n",
+    "#Calculations\n",
+    "pmi=aic*(Sc/l)#..................#Mean effective pressure in bar\n",
+    "IP=(n*pmi*L*(pi/4)*D*D*k*N*10)/6#..............#Indicated power in kW\n",
+    "print \"Indicated power = %0.2f kW\"%(pmi)\n",
+    "BP=((W-S)*pi*Db*N)/(60*1000)#............#Brake power in kW\n",
+    "print \"Brake power = %0.2f kW\"%(BP)\n",
+    "pmb=(BP*6)/(n*L*D*D*(pi/4)*k*N*10)#...........#Brake mean effective pressure in bar\n",
+    "print \"Brake mean effective pressure = %0.2f bar\"%(pmb)\n",
+    "bsfc=mf/BP#.................#Brake specific fuel consumption in kg/BP h\n",
+    "print \"Brake specific fuel consumption = %0.2f kg/BP h\"%bsfc\n",
+    "etabth=BP/((mf/3600)*C)#..................#Brake thermal efficiency\n",
+    "print \"Brake thermal efficiency = %0.2f %%\"%(etabth*100)\n",
+    "etaith=IP/((mf/3600)*C)#....................#Indicated thermal efficiency\n",
+    "print \"Indicated thermal efficiency = %0.2f %%\"%(etaith*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.34 PAGE 592"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 14,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Indicated thermal efficiency = 27.96 %\n",
+      "Mean effective pressure = 8.06 bar\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "R=287#................#Gas constant in J/kg K\n",
+    "n=4#...................#No of cylinders\n",
+    "D=0.0825#..............#Engine bore in m\n",
+    "L=0.13#................#Engine stroke in m\n",
+    "BP=28#..................#Brake power in kW\n",
+    "N=1500#.................#Engine rpm\n",
+    "afrth=14.8#...............#theoretical air fuel ratio \n",
+    "C=45980#..................#Calorific value of fuel in kJ/kg\n",
+    "etamech=0.9#.............#Mechanical efficiency\n",
+    "ap=70#..................#Percentage of Volume of air in he cylinder\n",
+    "fr=20#..................#Percentage richness of the fuel\n",
+    "p1=1.0132#.................#Ambient pressure in bar\n",
+    "pc=762#...................#Pressure in the cylinder in mm of Hg \n",
+    "tc=273+15.5#...............#Temperature in the cylinder in Kelvin\n",
+    "k=0.5#..................#Four stroke engine\n",
+    "#Calculations\n",
+    "Vs=(pi/4)*D*D*L#.......................#Swept volume in m**3\n",
+    "va=(ap/100)*Vs#.....................#Volume of air drawn in m**3\n",
+    "p=(pc/760)*p1#\n",
+    "m=(p*(10**5)*va)/(R*tc)#...................#Mass of air per stroke per cylinder\n",
+    "tmau=m*(N/2)*n#...................#Theoretical mass of air used per minute in kg\n",
+    "tmfu=tmau/afrth#..................#Theoretical mass of fyel used per min in kg\n",
+    "mf=(tmfu/60)*((100+fr)/100)#...............#Mass of fuel burnt per second in kg\n",
+    "IP=BP/etamech#.........................#Indicated power in kW\n",
+    "etaith=IP/(mf*C)#.....................#Indicated thermal efficiency \n",
+    "print \"Indicated thermal efficiency = %0.2f %%\"%(etaith*100)\n",
+    "pmb=(BP*6)/(n*L*D*D*(pi/4)*N*10*k)#...............#Mean effective pressure in bar\n",
+    "print \"Mean effective pressure = %0.2f bar\"%(pmb)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.35 PAGE 593"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 15,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Indicated power = 13.44 kW\n",
+      "Brake power = 10.76 kW\n",
+      "Indicated thermal efficiency = 23.87 %\n",
+      "Brake thermal efficiency = 19.11 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "n=1#..................#No of cylinders\n",
+    "D=0.2#............#Engine bore in m\n",
+    "L=0.4#..............#Engine stroke in m\n",
+    "Nt=9400#...............#Total no of revolutions \n",
+    "Ne=4200#...............#Total no of explosions\n",
+    "t=40#...................#Duration of testing in min\n",
+    "Nk=Ne/t#...............#No of explosions\n",
+    "bl=540#...............#Brake load in N\n",
+    "Db=1.6#.................#Diameter of brake wheel in m\n",
+    "d=0.02#................#Diameter of rope in m\n",
+    "gu=8.5#..................#Gas used in m**3/sec\n",
+    "C=15900#...............#Calorific value of fuel in kJ/kg\n",
+    "Vg=(gu/(t*60))#.................#Volume of gas used in m**3/sec\n",
+    "aic=550#.....................#Area of indicator diagram mm**2\n",
+    "l=72#.......................#Length of indicator diagram in mm\n",
+    "s=0.8#.....................#Spring number in bar/mm\n",
+    "#calculations\n",
+    "pmi=(aic*s)/l#................#Mean effective pressure in bar\n",
+    "IP=(n*pmi*L*D*D*(pi/4)*Nk*10)/6#............#Indicated power in kW\n",
+    "print \"Indicated power = %0.2f kW\"%(IP)\n",
+    "BP=(bl*pi*(Db+d)*(Nt/t))/(60*1000)#...............#Brake power in kW\n",
+    "print \"Brake power = %0.2f kW\"%(BP)\n",
+    "etaith=IP/(Vg*C)#...............#Indicated thermal efficiency\n",
+    "print \"Indicated thermal efficiency = %0.2f %%\"%(etaith*100)\n",
+    "etabth=BP/(Vg*C)#...............#Brake thermal efficiency\n",
+    "print \"Brake thermal efficiency = %0.2f %%\"%(etabth*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.36 PAGE 594"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 16,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Brake mean effective pressure = 3.97 bar\n",
+      "Brake specific fuel consumption = 0.30 kg/kWh\n",
+      "Brake thermal efficiency = 26.38 %\n",
+      "Volumetric efficiency = 61.01 %\n",
+      "Percentage of excess air supplied : 43.76\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi,sqrt\n",
+    "# Initialisation of Variables\n",
+    "n=6#....................#No of cylinders\n",
+    "D=0.125#................#Engine bore in m\n",
+    "L=0.125#...............#Engine stroke in m\n",
+    "N=2400#.................#Engine rpm\n",
+    "W=490#...............#Load on the dynamometer in N\n",
+    "CD=16100#...............#Dynamometer constant\n",
+    "d0=0.055#...................#Air orifice diameter in m\n",
+    "Cd=0.66#...................#Co efficient of discharge\n",
+    "hw=310#.................#Head causing flow through prifice in mm of water\n",
+    "br=760#................#Barometer reading in mm of Hg\n",
+    "t=298#..................#Ambient temperature in Kelvin\n",
+    "fc=22.1#..................#Fuel consumption per hour in kg\n",
+    "C=45100#..................#Calorific value of fuel used in kJ/kg\n",
+    "perc=85#...................#Percentage of carbon in the fuel\n",
+    "perh=15#...................#Percentage of hydrogen in the fuel\n",
+    "p1=1.013#....................#Pressure of air at the end of suction stroke in bar\n",
+    "t1=298#......................#Temperature of air the the end of suction stroke in Kelvin\n",
+    "k=0.5#.......................#Four stroke engine\n",
+    "R=287#.......................#Gas constant in J/kgK\n",
+    "#calculations\n",
+    "BP=W*(N/CD)#................#Brake power in kW\n",
+    "pmb=(BP*6)/(L*D*D*k*10*N*n*(pi/4))#................#Brake mean effective pressure in bar\n",
+    "print \"Brake mean effective pressure = %0.2f bar\"%(pmb)\n",
+    "bsfc=fc/BP#.......................#Brake specific fuel consumption in kg/kWh\n",
+    "print \"Brake specific fuel consumption = %0.2f kg/kWh\"%(bsfc)\n",
+    "etathb=BP/((fc/3600)*C)#......................#Brake thermal efficiency\n",
+    "print \"Brake thermal efficiency = %0.2f %%\"%(etathb*100)\n",
+    "Vst=(pi/4)*D*D*L#..............#Stroke volume in m**3\n",
+    "Val=840*(pi/4)*d0*d0*Cd*sqrt((hw/10)/((p1*10**5)/(R*t1)))#............#Volume of air passing through orifice of air box per min\n",
+    "Vac=Val/n#.........................#Actual volume of air per cylinder in m**3/min\n",
+    "asps=Vac/(N/2)#.......................#Air supplied per stroke per cylinder in m**3\n",
+    "etav=asps/Vst#....................#Volumetric efficiency\n",
+    "print \"Volumetric efficiency = %0.2f %%\"%(etav*100)\n",
+    "Qa=(100/23)*(((perc/100)*(8/3))+((perh/100)*(8/1)))#.....................#Quantity of air required per kg of fuel combustion\n",
+    "aqas=(Val*((p1*10**5)/(R*t1))*60)/fc#....................#Actual quantity of air supplied per kg of fuel\n",
+    "pe=(aqas-Qa)/Qa#....................#Fraction of excess air supplied to engine\n",
+    "print \"Percentage of excess air supplied : %0.2f\"%(pe*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.37 PAGE 595"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 17,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Mechanical efficiency = 77.28 %\n",
+      "Brake thermal efficiency = 23.26 %\n",
+      "HEAT BALANCE TABLE : \n",
+      "_______________________________________________________________________\n",
+      "Item                                      kJ                  Percent\n",
+      "_______________________________________________________________________\n",
+      "Heat supplied by fuel                     367840             100.00\n",
+      "Heat absorbed in IP                       110694             30.09\n",
+      "Heat taken away by cooling water          59774             16.25\n",
+      "Heat carried away by exhaust gases        197371             53.66\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "n=1#......................#No of cylinders\n",
+    "D=0.3#....................#Engine bore in m\n",
+    "L=0.45#....................#Engine stroke in m\n",
+    "mf=8.8#...................#Fuel consumption in kg/h\n",
+    "C=41800#...................#Calorific value of fuel in kJ/kg\n",
+    "N=200#....................#Engine rpm\n",
+    "pmi=5.8#....................#Mean effective pressure in bar\n",
+    "bl=1860#....................#Brake load in N\n",
+    "Db=1.22#...................#Diameter of brake drum in m\n",
+    "k=0.5#........................#four stroke engine\n",
+    "mw=650#......................#Mass of cooling water in kg\n",
+    "cpw=4.18#....................#Specific heat capacity of water\n",
+    "delt=22#......................#Temperature rise\n",
+    "#Calculations\n",
+    "IP=(n*L*D*D*k*10*pmi*N*(pi/4))/6#...............#Indicated power in kW\n",
+    "BP=(bl*pi*Db*N)/(60*1000)#..................#Brake power in kW\n",
+    "etamech=BP/IP#............#Mechanical efficiency\n",
+    "print \"Mechanical efficiency = %0.2f %%\"%(etamech*100)\n",
+    "etathb=BP/((mf/3600)*C)#...................#Brake thermal efficiency\n",
+    "print \"Brake thermal efficiency = %0.2f %%\"%(etathb*100)\n",
+    "#Heat supplied\n",
+    "hip=IP*3600#...........#Heat equivalent of IP in kJ/h\n",
+    "hcw=mw*cpw*delt#..........#Heat carried away by cooling water\n",
+    "hf=mf*C#................#heat supplied by fuel\n",
+    "hex=hf-hip-hcw#..........#Heat carried by exhaust gasses\n",
+    "pf=100#\n",
+    "pip=(hip/hf)*100#\n",
+    "pcw=(hcw/hf)*100#\n",
+    "pex=(hex/hf)*100\n",
+    "print \"HEAT BALANCE TABLE : \"\n",
+    "print \"_______________________________________________________________________\"\n",
+    "print \"Item                                      kJ                  Percent\"\n",
+    "print \"_______________________________________________________________________\"\n",
+    "print \"Heat supplied by fuel                     %d             %0.2f\"%(hf,pf)\n",
+    "print \"Heat absorbed in IP                       %d             %0.2f\"%(hip,pip)\n",
+    "print \"Heat taken away by cooling water          %d             %0.2f\"%(hcw,pcw)\n",
+    "print \"Heat carried away by exhaust gases        %d             %0.2f\"%(hex,pex)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.38 PAGE 596"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 18,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Brake power = 37.01 kW\n",
+      "Brake specific fuel consumption = 0.28 kg/kWh:\n",
+      "Brake thermal efficiency = 29.76 %\n",
+      "HEAT BALANCE TABLE:\n",
+      "_______________________________________________________________________\n",
+      "Item                                      kJ                  Percent\n",
+      "_______________________________________________________________________\n",
+      "Heat supplied by fuel                     7461             100.00\n",
+      "Heat absorbed in BP                       2220             29.76\n",
+      "Heat taken away by cooling water          2332             31.26\n",
+      "Heat carried away by exhaust gases        1811             24.28\n",
+      "Unaccounted heat                          1097             14.70\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "r=15#................#Compression ratio\n",
+    "n=1#...................#No of cylinders\n",
+    "mf=10.2#..................#Fuel consumption in kg/h\n",
+    "C=43890#.................#Calorific value of fuel in kJ/kg\n",
+    "ma=3.8#.................#Consumption of air in kg/min\n",
+    "N=1900#...................#Engine rpm\n",
+    "T=186#....................#Torque on brake drum in Nm\n",
+    "mw=15.5#.................#Mass of cooling water used in kg/min\n",
+    "delt=36#..................#temperature rise\n",
+    "tg=410#..................#Exhaust gas temperature in Celsius\n",
+    "tr=20#...................#Room temperature in Celsius\n",
+    "cp=1.17#.................#Specific heat capacity for exhaust gases kJ/kgK\n",
+    "cpw=4.18#..................#Specific heat capacity for water in kJ/kgK\n",
+    "#calculations\n",
+    "BP=(2*pi*N*T)/(60*1000)#................#Brake power in kW\n",
+    "print \"Brake power = %0.2f kW\"%BP\n",
+    "bsfc=mf/BP#.............................#Brake specific fuel consumption in kg/kWh\n",
+    "print \"Brake specific fuel consumption = %0.2f kg/kWh:\"%bsfc\n",
+    "etabth=BP/((mf/3600)*C)#....................#Brake thermal efficiency\n",
+    "print \"Brake thermal efficiency = %0.2f %%\"%(etabth*100)\n",
+    "#Heat supplied\n",
+    "mg=(mf/60)+ma#....................#Mass of exhaust gases in kg/min\n",
+    "hbp=BP*60#...........#Heat equivalent of BP in kJ/min\n",
+    "hcw=mw*cpw*delt#..........#Heat carried away by cooling water\n",
+    "hf=(mf/60)*C#................#heat supplied by fuel\n",
+    "hex=mg*cp*(tg-tr)#..........#Heat carried by exhaust gasses\n",
+    "ha=round(hf)-round(hbp+hex+hcw)#............#Unaccounted heat\n",
+    "pf=100#\n",
+    "pbp=(hbp/hf)*100#\n",
+    "pcw=(hcw/hf)*100#\n",
+    "pex=(hex/hf)*100#\n",
+    "pa=(ha/hf)*100#\n",
+    "print \"HEAT BALANCE TABLE:\"\n",
+    "print \"_______________________________________________________________________\"\n",
+    "print \"Item                                      kJ                  Percent\"\n",
+    "print \"_______________________________________________________________________\"\n",
+    "print \"Heat supplied by fuel                     %d             %0.2f\"%(hf,pf)\n",
+    "print \"Heat absorbed in BP                       %d             %0.2f\"%(hbp,pbp)\n",
+    "print \"Heat taken away by cooling water          %d             %0.2f\"%(hcw,pcw)\n",
+    "print \"Heat carried away by exhaust gases        %d             %0.2f\"%(hex,pex)\n",
+    "print \"Unaccounted heat                          %d             %0.2f\"%(ha,pa)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.39 PAGE 597"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 19,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Indicated power = 15.91 kW\n",
+      "Brake power = 11.73 kW\n",
+      "HEAT BALANCE TABLE\n",
+      "_______________________________________________________________________\n",
+      "Item                                          kJ               Percent\n",
+      "_______________________________________________________________________\n",
+      "Heat supplied by fuel                       66728             100.000000\n",
+      "Heat absorbed in IP                         19088             28.606158\n",
+      "Heat taken away by cooling water            16929             25.370159\n",
+      "Heat carried away by dry exhaust gases      13448             20.154897\n",
+      "Heat carried away by steam in exhaust gases 6606             9.901049\n",
+      "Unaccounted heat                            10655             15.967810\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "Cpw=4.18#..............#Specific heat of water in kJ/kgK\n",
+    "n=1#................#No of cylinders\n",
+    "N=350#.......#Engine rpm\n",
+    "pmi=3.1#..........#Mean effective pressure in bar\n",
+    "bl=640#..........#Brake load in N\n",
+    "mf=1.52#............#Fuel consumption in kg\n",
+    "mw=162#..............#Mass of cooling water\n",
+    "tw1=30#...............#Water inlet temperature in C\n",
+    "tw2=55#................#Water outlet temperature in C\n",
+    "ma=32#..................#Mass of air used per kg of fuel in kg\n",
+    "tr=25#.................#Room temperature in C\n",
+    "tg=305#.................#Exhaust temperature in C\n",
+    "D=0.2#.................#Engine bore in m\n",
+    "L=0.28#.................#Engine stroke in m\n",
+    "Db=1#......................#Brake drum diameter in m\n",
+    "ms=1.4#......................#Mass of steam formed per kg of fuel exhaust in kg\n",
+    "C=43900#...................#Calorirfic value of fuel in kJ/kg\n",
+    "Cps=2.09#..................#Specific heat of steamm in exhaust in kJ/kgK\n",
+    "Cpg=1.0#...................#Specific heat of dry exhaust gases in kJ/kgK\n",
+    "k=1#....................#Two stroke engiine\n",
+    "t=20#.....................#Duration of testing in min\n",
+    "#Calculations\n",
+    "IP=(n*pmi*N*D*D*L*k*10*(pi/4))/6#...................#Indicated power in kW\n",
+    "print \"Indicated power = %0.2f kW\"%IP\n",
+    "BP=(bl*pi*Db*N)/(60*1000)#......................#Brake power in kW\n",
+    "print \"Brake power = %0.2f kW\"%BP\n",
+    "#Heat supplied\n",
+    "hf=mf*C#................#heat supplied by fuel\n",
+    "hip=IP*60*t#...........#Heat equivalent of BP in kJ/min\n",
+    "hcw=mw*Cpw*(tw2-tw1)#..........#Heat carried away by cooling water\n",
+    "mg=mf+(ma*mf)#....................#Mass of exhaust gases in kg/min\n",
+    "mst=mf*ms#..................#Mass of steam formed\n",
+    "hg=(mg-mst)*Cpg*(tg-tr)#..........#Heat carried by exhaust gasses\n",
+    "hst=mst*(417.5+2257.9+(Cps*(305-99.6)))#....................#Heat carried by exhaust steam, the obtained values are from steam table and hence are constants at NTP\n",
+    "ha=round(hf)-round(hip+hg+hst+hcw)#............#Unaccounted heat\n",
+    "pf=100#\n",
+    "pip=(hip/hf)*100#\n",
+    "pcw=(hcw/hf)*100#\n",
+    "pg=(hg/hf)*100#\n",
+    "pa=(ha/hf)*100#\n",
+    "pst=(hst/hf)*100#\n",
+    "print \"HEAT BALANCE TABLE\"\n",
+    "print \"_______________________________________________________________________\"\n",
+    "print \"Item                                          kJ               Percent\"\n",
+    "print \"_______________________________________________________________________\"\n",
+    "print \"Heat supplied by fuel                       %d             %f\"%(hf,pf)\n",
+    "print \"Heat absorbed in IP                         %d             %f\"%(hip,pip)\n",
+    "print \"Heat taken away by cooling water            %d             %f\"%(hcw,pcw)\n",
+    "print \"Heat carried away by dry exhaust gases      %d             %f\"%(hg,pg)\n",
+    "print \"Heat carried away by steam in exhaust gases %d             %f\"%(hst,pst)\n",
+    "print \"Unaccounted heat                            %d             %f\"%(ha,pa)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.40 PAGE 598"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 20,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Volumetric efficiency = 68.49 %\n",
+      "Brake mean effective pressure = 5.14 bar\n",
+      "Engine torque = 269.63 N-m\n",
+      "Brake specific fuel consumption = 0.27 kg/kWh\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi,sqrt\n",
+    "# Initialisation of Variables\n",
+    "n=6#................#No of cylinders\n",
+    "D=0.1#...............#Engine bore in m\n",
+    "L=0.14#...............#Engine stroke in m\n",
+    "N=2500#...............#Engine rpm\n",
+    "k=0.5#..................#Four stroke\n",
+    "bl=480#.................#Brake load in N\n",
+    "br=76#..................#Barometer reading in cm of Hg\n",
+    "d0=3.3/100#..............#Orifice diameter in m\n",
+    "Cd=0.62#.................#Co efficient of discharge of orifice\n",
+    "pd=14#...................#Pressure drop across orifice in cm of Hg\n",
+    "tr=25#...............#Room temperature in C\n",
+    "mf=0.32#................#Fuel consumption in kg/min\n",
+    "rhohg=13600#.................#Density of Hg in kg/m**3\n",
+    "R=0.287#...................#gas constant in kJ/kgK\n",
+    "g=9.81#.................#Acceleration due to gravity in m/s**2\n",
+    "CD=17000#....................#dynamometer constant\n",
+    "#Calculations\n",
+    "Vs=(pi/4)*D*D*L*(N/2)*(n/60)#..............#Swept volume in m**3\n",
+    "br1=(br/100)*rhohg*g*(10**-3)#.............#Barometer reading into kN/m**2\n",
+    "rhoa=br1/(R*(tr+273))#...............#Density of air\n",
+    "pd1=(pd/100)*rhohg*g#......................#Conversion of pd into N/m**2\n",
+    "ha=pd1/(rhoa*g)#.......................#Head of air causing flow in m\n",
+    "Va=Cd*(pi/4)*d0*d0*sqrt(2*g*ha)#............#Volume of air passing through orifice of air box per min\n",
+    "etav=Va/Vs#....................#Volumetric efficiency\n",
+    "print \"Volumetric efficiency = %0.2f %%\"%(etav*100)\n",
+    "BP=bl*(N/CD)#................#Brake power in kW\n",
+    "pmb=(BP*6)/(L*D*D*k*10*N*n*(pi/4))#................#Brake mean effective pressure in bar\n",
+    "print \"Brake mean effective pressure = %0.2f bar\"%(pmb)\n",
+    "T=(BP*60*1000)/(2*pi*N)#....................#Engine torque in N-m\n",
+    "print \"Engine torque = %0.2f N-m\"%T\n",
+    "bsfc=(mf*60)/BP#.......................#Brake specific fuel consumption in kg/kWh\n",
+    "print \"Brake specific fuel consumption = %0.2f kg/kWh\"%bsfc"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.41 PAGE 598"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 21,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Indicated power = 14.06 kW\n",
+      "Indicated thermal efficiency = 26.85 %\n",
+      "HEAT BALANCE TABLE\n",
+      "_______________________________________________________________________\n",
+      "Item                                          kJ               Percent\n",
+      "_______________________________________________________________________\n",
+      "Heat supplied by fuel                       3141.79             100.00\n",
+      "Heat equivalent of BP                       659.73             21.00\n",
+      "Heat taken away by cooling water            862.12             27.44\n",
+      "Heat carried away by dry exhaust gases      782.78             24.92\n",
+      "Heat carried away by steam in exhaust gases 294.85             9.38\n",
+      "Unaccounted heat                            543.00             17.28\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "Cpw=4.18#..............#Specific heat of water in kJ/kgK\n",
+    "n=1#................#No of cylinders\n",
+    "N=350#.......#Engine rpm\n",
+    "pmi=2.74#..........#Mean effective pressure in bar\n",
+    "bl=600#..........#Brake load in N\n",
+    "mf=4.22#............#Fuel consumption in kg\n",
+    "mw=495#..............#Mass of cooling water\n",
+    "tw1=13#...............#Water inlet temperature in C\n",
+    "tw2=38#................#Water outlet temperature in C\n",
+    "ma=135#..................#Mass of air used in kg/h\n",
+    "tr=20#.................#Room temperature in C\n",
+    "tg=370#.................#Exhaust temperature in C\n",
+    "D=0.2#.................#Engine bore in m\n",
+    "L=0.28#.................#Engine stroke in m\n",
+    "Db=1#......................#Brake drum diameter in m\n",
+    "C=44670#...................#Calorirfic value of fuel in kJ/kg\n",
+    "Cps=2.093#..................#Specific heat of steamm in exhaust in kJ/kgK\n",
+    "Cpg=1.005#...................#Specific heat of dry exhaust gases in kJ/kgK\n",
+    "k=1#....................#Two stroke engiine\n",
+    "t=60#.....................#Duration of testing in min\n",
+    "perh=15#.................#Percentage of H2 in the fuel\n",
+    "#Calculations\n",
+    "IP=(n*pmi*N*D*D*L*k*10*(pi/4))/6#...................#Indicated power in kW\n",
+    "print \"Indicated power = %0.2f kW\"%IP\n",
+    "BP=(bl*pi*Db*N)/(60*1000)#......................#Brake power in kW\n",
+    "etaith=(IP)/((mf/3600)*C)#.................#Indicated thermal efficiency\n",
+    "print \"Indicated thermal efficiency = %0.2f %%\"%(etaith*100)\n",
+    "#Heat supplied\n",
+    "hf=(mf/t)*C#................#heat supplied by fuel\n",
+    "hbp=BP*t#...........#Heat equivalent of BP in kJ/min\n",
+    "hcw=(mw/60)*Cpw*(tw2-tw1)#..........#Heat carried away by cooling water\n",
+    "mg=(mf+ma)/t#....................#Mass of exhaust gases in kg/min\n",
+    "mst=9*(perh/100)*(mf/60)#..................#Mass of steam formed\n",
+    "mdg=mg-mst#..............................#Mass of dry exhaust gases per min\n",
+    "hg=(mdg)*Cpg*(tg-tr)#..........#Heat carried by exhaust gasses\n",
+    "hst=mst*(417.5+2257.9+(Cps*(305-99.6)))#....................#Heat carried by exhaust steam, the obtained values are from steam table and hence are constants at NTP\n",
+    "ha=round(hf)-round(hbp+hg+hst+hcw)#............#Unaccounted heat\n",
+    "pf=100#\n",
+    "pbp=(hbp/hf)*100#\n",
+    "pcw=(hcw/hf)*100#\n",
+    "pg=(hg/hf)*100#\n",
+    "pa=(ha/hf)*100#\n",
+    "pst=(hst/hf)*100#\n",
+    "print \"HEAT BALANCE TABLE\"\n",
+    "print \"_______________________________________________________________________\"\n",
+    "print \"Item                                          kJ               Percent\"\n",
+    "print \"_______________________________________________________________________\"\n",
+    "print \"Heat supplied by fuel                       %0.2f             %0.2f\"%(hf,pf)\n",
+    "print \"Heat equivalent of BP                       %0.2f             %0.2f\"%(hbp,pbp)\n",
+    "print \"Heat taken away by cooling water            %0.2f             %0.2f\"%(hcw,pcw)\n",
+    "print \"Heat carried away by dry exhaust gases      %0.2f             %0.2f\"%(hg,pg)\n",
+    "print \"Heat carried away by steam in exhaust gases %0.2f             %0.2f\"%(hst,pst)\n",
+    "print \"Unaccounted heat                            %0.2f             %0.2f\"%(ha,pa)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.42 PAGE 599"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 22,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Indicated power = 17.38 kW\n",
+      "Brake power = 10.81 kW\n",
+      "HEAT BALANCE TABLE : \n",
+      "_______________________________________________________________________\n",
+      "Item                                          kJ               Percent\n",
+      "_______________________________________________________________________\n",
+      "Heat supplied by fuel                       3146             100.00\n",
+      "Heat absorbed in IP                         1043             33.15\n",
+      "Heat taken away by cooling water            870             27.68\n",
+      "Heat carried away by dry exhaust gases      877             27.89\n",
+      "Heat carried away by steam in exhaust gases 319             10.16\n",
+      "Unaccounted heat                            35             1.11\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "Cpw=4.18#..............#Specific heat of water in kJ/kgK\n",
+    "n=1#................#No of cylinders\n",
+    "N=350#.......#Engine rpm\n",
+    "pmi=2.8#..........#Mean effective pressure in bar\n",
+    "bl=590#..........#Brake load in N\n",
+    "mf=4.3#............#Fuel consumption in kg\n",
+    "mw=500#..............#Mass of cooling water\n",
+    "tw1=25#...............#Water inlet temperature in C\n",
+    "tw2=50#................#Water outlet temperature in C\n",
+    "ma=33#..................#Mass of air used per kg of fuel in kg\n",
+    "tr=25#.................#Room temperature in C\n",
+    "tg=400#.................#Exhaust temperature in C\n",
+    "D=0.22#.................#Engine bore in m\n",
+    "L=0.28#.................#Engine stroke in m\n",
+    "Db=1#......................#Brake drum diameter in m\n",
+    "C=43900#...................#Calorirfic value of fuel in kJ/kg\n",
+    "Cps=2.09#..................#Specific heat of steamm in exhaust in kJ/kgK\n",
+    "Cpg=1.0#...................#Specific heat of dry exhaust gases in kJ/kgK\n",
+    "k=1#....................#Two stroke engiine\n",
+    "perh=15#...................#Percentage of hydrogen\n",
+    "#Calculations\n",
+    "IP=(n*pmi*N*D*D*L*k*10*(pi/4))/6#...................#Indicated power in kW\n",
+    "print \"Indicated power = %0.2f kW\"%IP\n",
+    "BP=(bl*pi*Db*N)/(60*1000)#......................#Brake power in kW\n",
+    "print \"Brake power = %0.2f kW\"%BP\n",
+    "#Heat supplied\n",
+    "hf=(mf/60)*C#................#heat supplied by fuel\n",
+    "hip=IP*60#...........#Heat equivalent of BP in kJ/min\n",
+    "hcw=(mw/60)*Cpw*(tw2-tw1)#..........#Heat carried away by cooling water\n",
+    "mg=(mf+(mf*ma))/60#....................#Mass of exhaust gases in kg/min\n",
+    "mst=9*(perh/100)*(mf/60)#..................#Mass of steam formed\n",
+    "mdg=mg-mst#..............................#Mass of dry exhaust gases per min\n",
+    "hg=(mdg)*Cpg*(tg-tr)#..........#Heat carried by exhaust gasses\n",
+    "hst=mst*(417.5+2257.9+(Cps*(400-99.6)))#....................#Heat carried by exhaust steam, the obtained values are from steam tables at NTP\n",
+    "mg=mf+(ma*mf)#....................#Mass of exhaust gases in kg/min\n",
+    "ha=round(hf)-round(hip+hg+hst+hcw)#............#Unaccounted heat\n",
+    "pf=100#\n",
+    "pip=(hip/hf)*100#\n",
+    "pcw=(hcw/hf)*100#\n",
+    "pg=(hg/hf)*100#\n",
+    "pa=(ha/hf)*100#\n",
+    "pst=(hst/hf)*100#\n",
+    "print \"HEAT BALANCE TABLE : \"\n",
+    "print \"_______________________________________________________________________\"\n",
+    "print \"Item                                          kJ               Percent\"\n",
+    "print \"_______________________________________________________________________\"\n",
+    "print \"Heat supplied by fuel                       %d             %0.2f\"%(hf,pf)\n",
+    "print \"Heat absorbed in IP                         %d             %0.2f\"%(hip,pip)\n",
+    "print \"Heat taken away by cooling water            %d             %0.2f\"%(hcw,pcw)\n",
+    "print \"Heat carried away by dry exhaust gases      %d             %0.2f\"%(hg,pg)\n",
+    "print \"Heat carried away by steam in exhaust gases %d             %0.2f\"%(hst,pst)\n",
+    "print \"Unaccounted heat                            %d             %0.2f\"%(ha,pa)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.43 PAGE 600"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 23,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "HEAT BALANCE TABLE: \n",
+      "_______________________________________________________________________\n",
+      "Item                                      kJ                  Percent\n",
+      "_______________________________________________________________________\n",
+      "Heat supplied by fuel                     7951             100.00\n",
+      "Heat absorbed in BP                       3073             21.00\n",
+      "Heat taken away by cooling water          2544             27.68\n",
+      "Heat carried away by exhaust gases        1745             27.89\n",
+      "Unaccounted heat                          589             1.11\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "I=210#.....................#Output of generator in A\n",
+    "V=200#.....................#Generator voltage in V\n",
+    "etag=0.82#.................#Generator efficiency \n",
+    "mf=11.2#....................#Fuel used in kg/h\n",
+    "C=42600#.......................#Calorific value of fuel in kJ/kg\n",
+    "afr=18#....................#Air fuel ratio\n",
+    "mc=580#.....................#Mass of water through calorimeter in kg/h\n",
+    "delt=36#....................#Temperature raise in C\n",
+    "tg=98#........................#Temperature of exhaust in C\n",
+    "ta=20#.......................#Ambient temperature in C\n",
+    "phcw=0.32#.....................#Heat lost to cooling jacket is 32% of heat supplied\n",
+    "cpe=1.05#...................#Specific heat of exhause gases in kJ/kgK\n",
+    "cpw=4.18#...................#Specific heat of water in kJ/kgK\n",
+    "#Calculations\n",
+    "pow=V*I#......................#Total power generated in W\n",
+    "BP=(pow/1000)/etag#..................#Brake power in kW\n",
+    "hf=(mf/60)*C#...................#Heat supplied to the engine\n",
+    "hbp=BP*60#.........................#Heat equivalent of BP\n",
+    "mg=(mf/60)*(afr+1)#...............#Mass of exhaust gases formed per min in kg\n",
+    "hg=((mc/60)*cpw*(delt))+(mg*cpe*(tg-ta))#..........#Heat carried by exhaust gases per min\n",
+    "hcw=phcw*hf#...................#Heat lost to cooling jacket\n",
+    "ha=hf-(hcw+hg+hbp)#...................#Unaccounted heat\n",
+    "pf=100#pbp=(hbp/hf)*100#pcw=(hcw/hf)*100#pg=(hg/hf)*100#pa=(ha/hf)*100\n",
+    "print \"HEAT BALANCE TABLE: \"\n",
+    "print \"_______________________________________________________________________\"\n",
+    "print \"Item                                      kJ                  Percent\"\n",
+    "print \"_______________________________________________________________________\"\n",
+    "print \"Heat supplied by fuel                     %d             %0.2f\"%(hf,pf)\n",
+    "print \"Heat absorbed in BP                       %d             %0.2f\"%(hbp,pbp)\n",
+    "print \"Heat taken away by cooling water          %d             %0.2f\"%(hcw,pcw)\n",
+    "print \"Heat carried away by exhaust gases        %d             %0.2f\"%(hg,pg)\n",
+    "print \"Unaccounted heat                          %d             %0.2f\"%(ha,pa)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.44 PAGE 601"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 24,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "HEAT BALANCE TABLE : \n",
+      "_______________________________________________________________________\n",
+      "Item                                          kJ               Percent\n",
+      "_______________________________________________________________________\n",
+      "Heat supplied by fuel                       8745             100.00\n",
+      "Heat absorbed in BP                         3056             34.95\n",
+      "Heat lost by FP                             658              7.53\n",
+      "Heat taken away by cooling water            2612             29.87\n",
+      "Heat carried away by dry exhaust gases      1569             17.94\n",
+      "Heat carried away by steam in exhaust gases 795              9.10\n",
+      "Unaccounted heat                            52               0.60\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "D=0.34#..............#Engine bore in m\n",
+    "k=0.5#...............#Four stroke engine\n",
+    "n=1#..................#No of cylinders\n",
+    "L=0.44#................#Engine stroke in m\n",
+    "Ne=400#................#Engine rpm\n",
+    "aic=465#..............#Area of indicator diagram in mm**2\n",
+    "l=60#..................#Length of diagram in mm\n",
+    "s=0.6#...............#Spring constant in bar/mm\n",
+    "W=950#.................#Load of dynamometer in N\n",
+    "CD=7460#................#Dynamometer constant\n",
+    "mf=10.6#................#Fuel used in kg/h\n",
+    "Ca=49500#.................#Calorific value of fuel in kJ/kg\n",
+    "mw=25#...................#Cooling water circulated in kg/min\n",
+    "cpw=4.18#..................#Specific heat capacity of water in kJ/kgC\n",
+    "delt=25#..................#Rise in temperature of water\n",
+    "#Mass analysis of fuel\n",
+    "C=84#..................#Percentage of carbon\n",
+    "H=15#..................#Percentage of hydrogen\n",
+    "In=1#..................#Percentage of incombustible\n",
+    "#Volume analysis of exhaust gases\n",
+    "CO2=9#..................#Percentage of caron dioxide\n",
+    "O=10#..................#Percentage of oxygen\n",
+    "N=81#..................#Percentage of nitrogen\n",
+    "tg=400#................#Temperature of exhaust gases in C\n",
+    "cpg=1.05#..............#Specific heat of exhaust gases in kJ/kgC\n",
+    "tr=25#.................#Temperature of room in C\n",
+    "ppst=0.03#..............#Partial pressure of steam in exhaust gases in bar\n",
+    "cpst=2.1#.................#Specific heat of superheated steam in kJ/kgC\n",
+    "#Calculations\n",
+    "pmi=(aic*s)/l#................#Mean effective pressure in bar\n",
+    "IP=(n*pmi*L*D*D*k*10*Ne*(pi/4))/6#...............#Indicated power in kW\n",
+    "BP=(W*Ne)/CD#.......................#Brake power in kW\n",
+    "FP=IP-BP#...........................#Frictional power in kW\n",
+    "hf=(mf/60)*Ca#...................#Heat supplied in kJ per min\n",
+    "hbp=BP*60#.....................#Heat equivalent of Brake power in kW\n",
+    "hfp=FP*60#......................#heat equivalent of frictional power in kW\n",
+    "hcw=mw*cpw*delt#..................#Heat carried away by cooling water\n",
+    "ma1=(N*C)/(33*(CO2))#...........#Mass of air supplied per kg of fuel\n",
+    "mg1=ma1+1#.......................#Mass of exhaust gases per kg of fuel\n",
+    "mg=mg1*(mf/60)#.................#Mass of exhaust gas formed per min\n",
+    "mst1=9*(H/100)#.................#Mass of steam formed per kg of fuel\n",
+    "mst=mst1*(mf/60)#..................#Mass of steam formed per min\n",
+    "mdg=mg-mst#.......................#Mass of dry exhaust gas \n",
+    "Hex=mdg*cpg*(tg-tr)#...............#Heat carried by exhaust gases\n",
+    "hst=(2545.5+(cpst*(tg-24.1)))*mst#................#Heat carried by steam in exhaust gases in kJ/kg.....The values are from steam tables corresponding to the partial pressure 0.03 and temperature 400 Celsius\n",
+    "ha=hf-(hbp+hfp+hcw+Hex+hst)#.....................#Unaccounted heat\n",
+    "pf=100#\n",
+    "pbp=(hbp/hf)*100#\n",
+    "pfp=(hfp/hf)*100#\n",
+    "pcw=(hcw/hf)*100#\n",
+    "pex=(Hex/hf)*100#\n",
+    "pa=(ha/hf)*100#\n",
+    "pst=(hst/hf)*100#\n",
+    "print \"HEAT BALANCE TABLE : \"\n",
+    "print \"_______________________________________________________________________\"\n",
+    "print \"Item                                          kJ               Percent\"\n",
+    "print \"_______________________________________________________________________\"\n",
+    "print \"Heat supplied by fuel                       %d             %0.2f\"%(hf,pf)\n",
+    "print \"Heat absorbed in BP                         %d             %0.2f\"%(hbp,pbp)\n",
+    "print \"Heat lost by FP                             %d              %0.2f\"%(hfp,pfp)\n",
+    "print \"Heat taken away by cooling water            %d             %0.2f\"%(hcw,pcw)\n",
+    "print \"Heat carried away by dry exhaust gases      %d             %0.2f\"%(Hex,pex)\n",
+    "print \"Heat carried away by steam in exhaust gases %d              %0.2f\"%(hst,pst)\n",
+    "print \"Unaccounted heat                            %d               %0.2f\"%(ha,pa)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.45 PAGE 602"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 25,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Mechanical efficiency = 83.29 %\n",
+      "Indicated thermal efficiency = 13.44 %\n",
+      "Air standard efficiency = 49.13 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "n=4#........................#No of cylinders\n",
+    "ga=1.4#...................#Degree of freedom\n",
+    "D=0.075#..................#Engine bore in m\n",
+    "L=0.1#...................#Engine stroke in m\n",
+    "mf=6#.......................#Fuel consumption in kg/h\n",
+    "C=83600#..................#Calorific value of fuel used\n",
+    "Vc=0.0001#.................#Clearence volume in m**3\n",
+    "BP=15.6#.................#Brake power wilh all cylinder working in kW\n",
+    "BP1=11.1#...................#Brake power wilh cylinder no 1 cutout in kW\n",
+    "BP2=11.03#...................#Brake power wilh cylinder no 2 cutout in kW\n",
+    "BP3=10.88#...................#Brake power wilh cylinder no 3 cutout in kW\n",
+    "BP4=10.66#...................#Brake power wilh cylinder no 4 cutout in kW\n",
+    "#Calculations\n",
+    "IP1=BP-BP1#...........................#Indicated power produced in cylinder 1 in kW\n",
+    "IP2=BP-BP2#...........................#Indicated power produced in cylinder 2 in kW\n",
+    "IP3=BP-BP3#...........................#Indicated power produced in cylinder 3 in kW\n",
+    "IP4=BP-BP4#...........................#Indicated power produced in cylinder 4 in kW\n",
+    "IP=IP1+IP2+IP3+IP4#.............................#Total Indicated power produced in kW\n",
+    "etamech=BP/IP#..............................#Mechanical efficiency\n",
+    "print \"Mechanical efficiency = %0.2f %%\"%(etamech*100)\n",
+    "etaith=IP/((mf/3600)*C)#.....................#Indicated thermal efficiency\n",
+    "print \"Indicated thermal efficiency = %0.2f %%\"%(etaith*100)\n",
+    "Vs=(pi/4)*D*D*L#..........................#Stroke volume in m**3\n",
+    "r=(Vs+Vc)/Vc#................................#Compression ratio\n",
+    "etast=1-(1/(r**(ga-1)))#...........................#Air standard efficiency\n",
+    "print \"Air standard efficiency = %0.2f %%\"%(etast*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 17.46 PAGE 603"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 26,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Engine torque = 59.20 Nm:\n",
+      "Brake mean effective pressure = 7.31 bar\n",
+      "Brake thermal efficiency = 21.31 %\n",
+      "Specific fuel consumption = 0.38 kg/kWh\n",
+      "Mechanical efficiency = 76.56 %\n",
+      "Indicated mean effective pressure = 9.55 bar \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "n=4#..........................#No of cylinders\n",
+    "D=0.06#......................#Engine bore in m\n",
+    "L=0.09#.......................#Engine stroke in m\n",
+    "N=2800#.......................#Engine rpm\n",
+    "Ta=0.37#.......................#Length of torque arm in m\n",
+    "spgr=0.74#.....................#Specific graviy of fuel \n",
+    "fc=8.986#......................#Fuel consumption in ltrs/h\n",
+    "mf=fc*spgr#.....................#Fuel consumed in kg/h\n",
+    "C=44100#......................#Calorific value of fuel in kJ/kg\n",
+    "BPnl=160#.................#Net brake load in N\n",
+    "BP1=110#...................#Brake load with cylinder no 1 cutout in N\n",
+    "BP2=107#...................#Brake load with cylinder no 2 cutout in N\n",
+    "BP3=104#...................#Brake load with cylinder no 3 cutout in N\n",
+    "BP4=110#...................#Brake load with cylinder no 4 cutout in N\n",
+    "k=0.5#.....................#Four stroke engine\n",
+    "#Calculations\n",
+    "T=BPnl*Ta#.......................#Engine torque in N-m\n",
+    "print \"Engine torque = %0.2f Nm:\"%T\n",
+    "BP=(2*pi*N*T)/(60*1000)#..........................#Brake power in kW\n",
+    "pmb=(BP*6)/(n*D*D*L*N*10*(pi/4)*k)#...................#Brake mean effective pressure in bar\n",
+    "print \"Brake mean effective pressure = %0.2f bar\"% pmb\n",
+    "etabth=BP/((mf/3600)*C)#...........................#Brake thermal efficiency\n",
+    "print \"Brake thermal efficiency = %0.2f %%\"%(etabth*100)\n",
+    "sfc=mf/BP#.......................#Specific fuel consumption in kg/kWh\n",
+    "print \"Specific fuel consumption = %0.2f kg/kWh\"%sfc\n",
+    "IP1=BPnl-BP1#...........................#Indicated power produced in cylinder 1 in kW\n",
+    "IP2=BPnl-BP2#...........................#Indicated power produced in cylinder 2 in kW\n",
+    "IP3=BPnl-BP3#...........................#Indicated power produced in cylinder 3 in kW\n",
+    "IP4=BPnl-BP4#...........................#Indicated power produced in cylinder 4 in kW\n",
+    "IP=IP1+IP2+IP3+IP4#.............................#Total Indicated power produced in kW\n",
+    "etamech=BPnl/IP#..............................#Mechanical efficiency\n",
+    "print \"Mechanical efficiency = %0.2f %%\"%(etamech*100)\n",
+    "pmi=pmb/etamech#............................#Indicated mean effective pressure in bar\n",
+    "print \"Indicated mean effective pressure = %0.2f bar \"%pmi"
+   ]
+  }
+ ],
+ "metadata": {
+  "kernelspec": {
+   "display_name": "Python 2",
+   "language": "python",
+   "name": "python2"
+  },
+  "language_info": {
+   "codemirror_mode": {
+    "name": "ipython",
+    "version": 2
+   },
+   "file_extension": ".py",
+   "mimetype": "text/x-python",
+   "name": "python",
+   "nbconvert_exporter": "python",
+   "pygments_lexer": "ipython2",
+   "version": "2.7.9"
+  }
+ },
+ "nbformat": 4,
+ "nbformat_minor": 0
+}
diff --git a/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER20_2.ipynb b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER20_2.ipynb
new file mode 100644
index 00000000..c3338c53
--- /dev/null
+++ b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER20_2.ipynb
@@ -0,0 +1,2548 @@
+{
+ "cells": [
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "# CHAPTER 20 - Air Compressors"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.1 PAGE 750"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 11,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Indicated power = 4.24 kW\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "v1=1#.........#Volume of air taken in m**3/min\n",
+    "p1=1.013#...............#Intake pressure in bar\n",
+    "t1=288#...............#Intake temperature in K\n",
+    "p2=7#......................#Delivery pressure in bar\n",
+    "n=1.35#..............#Adiabatic index\n",
+    "R=287#..............#Gas constant in kJ/kgK\n",
+    "#Calculations\n",
+    "m=(p1*v1*10**5)/(R*t1)#..............#Mass of air delivered per min in kg\n",
+    "t2=t1*((p2/p1)**((n-1)/n))#...........#Delivery temperature in K\n",
+    "iw=(n/(n-1))*m*R*(t2-t1)#............#Indicated work in kJ/min\n",
+    "IP=iw/(60*1000)#....................#Indicated power\n",
+    "print \"Indicated power = %0.2f kW\"%IP"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.2 PAGE 750"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 12,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Cylinder bore = 141.44 mm\n",
+      "Motor power = 5.54 kW\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "N=300#............#Compressor rpm\n",
+    "afr=15#.........#Air fuel ratio\n",
+    "etamech=0.85#....#Mechanical efficiency\n",
+    "etamt=0.9#.......#Motor transmission efficiency\n",
+    "v=1#............#Volume dealt with per min at inlet in m**3/min\n",
+    "rld=1.5#........#Ratio of stroke to diameter\n",
+    "v1=1#.........#Volume of air taken in m**3/min\n",
+    "p1=1.013#...............#Intake pressure in bar\n",
+    "t1=288#...............#Intake temperature in K\n",
+    "p2=7#......................#Delivery pressure in bar\n",
+    "n=1.35#..............#Adiabatic index\n",
+    "R=287#..............#Gas constant in kJ/kgK\n",
+    "#Calculations\n",
+    "m=(p1*v1*10**5)/(R*t1)#..............#Mass of air delivered per min in kg\n",
+    "t2=t1*((p2/p1)**((n-1)/n))#...........#Delivery temperature in K\n",
+    "iw=(n/(n-1))*m*R*(t2-t1)#............#Indicated work in kJ/min\n",
+    "IP=iw/(60*1000)#....................#Indicated power in kW\n",
+    "vdc=v/N#........#Volume drawn in per cycle in m**3\n",
+    "D=(vdc/((pi/4)*rld))**(1/3)#..........#Cylinder bore in m\n",
+    "print \"Cylinder bore = %0.2f mm\"%(D*1000)\n",
+    "pc=IP/etamech#.........#Power input to the compressor in kW\n",
+    "mp=pc/etamt#..........#Motor power in kW\n",
+    "print \"Motor power = %0.2f kW\"%mp"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.3 PAGE 751"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 13,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Temperature at the end of compression = 430.07 K\n",
+      "Work done during compression per kg of air = 236.03 kJ\n",
+      "Heat transferred during compression per kg of air = -98.28 kJ\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "p1=1#......#Suction pressure in bar\n",
+    "t1=293#.....#Suction temperature in K\n",
+    "n=1.2#......#Compression index\n",
+    "p2=10#......#Delivery pressure in bar\n",
+    "R=0.287#....#Gas constant in kJ/kgK\n",
+    "cv=0.718#...#Specific heat at constant volume in kJ/kgK\n",
+    "#Calculations\n",
+    "t2=t1*((p2/p1)**((n-1)/n))#.....#Temperature at the end of compression in K\n",
+    "print \"Temperature at the end of compression = %0.2f K\"%t2\n",
+    "W=1*R*t1*(n/(n-1))*(((p2/p1)**((n-1)/n))-1)#.......#Work done during compression of air in kJ\n",
+    "print \"Work done during compression per kg of air = %0.2f kJ\"%W\n",
+    "Q=(t2-t1)*(cv-((R)/(n-1)))#..........#Heat transferred during compression of air in kJ/kg\n",
+    "print \"Heat transferred during compression per kg of air = %0.2f kJ\"%Q"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.4 PAGE 752"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 14,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Volumetric Efficiency = 77.39 %\n",
+      "Indicated power = 5.35 kW\n",
+      "Isothermal efficiency = 79.79 %\n",
+      "Mechanical efficiency = 85.60 %\n",
+      "Overall efficiency = 68.30 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt,log\n",
+    "# Initialisation of Variables\n",
+    "p1=1#........#Suction pressure in bar\n",
+    "t1=293#.......#Suction temperature in K\n",
+    "p2=6#..........#Discharge pressure in bar\n",
+    "t2=453#.......#Discharge temperature in K\n",
+    "N=1200#.........#Compressor rpm\n",
+    "Ps=6.25#........#Shaft power in kW\n",
+    "ma=1.7#........#Mass of air delivered in kg/min\n",
+    "D=0.14#......#Engine bore in m\n",
+    "L=0.10#.......#Engine stroke in m\n",
+    "R=287#..........#Gas constant in kJ/kgK\n",
+    "#Calculations\n",
+    "Vd=(pi/4)*D*D*L*N#.........#Displlacement volume in m**3/min\n",
+    "FAD=ma*R*t1/(p1*10**5)#........#Free air delivered\n",
+    "etav=FAD/Vd#.....#Volumetric efficiency \n",
+    "print \"Volumetric Efficiency = %0.2f %%\"%(etav*100)\n",
+    "n=1/(1-((log(t2/t1))/(log(p2/p1))))#........#Index of compression\n",
+    "IP=(n/(n-1))*(ma/60)*(R/1000)*t1*(((p2/p1)**((n-1)/n))-1)#..........#Indicated power in kW\n",
+    "print \"Indicated power = %0.2f kW\"%IP\n",
+    "Piso=((ma/60)*(R/1000)*t1*(log(p2/p1)))#..........#Isothermal power\n",
+    "etaiso=Piso/IP#..............#Isothermal efficiency\n",
+    "print \"Isothermal efficiency = %0.2f %%\"%(etaiso*100)\n",
+    "etamech=IP/Ps#...........#Mechanical efficiency\n",
+    "print \"Mechanical efficiency = %0.2f %%\"%(etamech*100)\n",
+    "etao=Piso/Ps#........#Overall efficiency\n",
+    "print \"Overall efficiency = %0.2f %%\"%(etao*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.5 PAGE 753"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 1,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Work output = 148.95 kW\n",
+      "Mass of cooling water = 2.12 kg/min\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "ma=6.75#.........#Mass of air compressed in kg/min\n",
+    "p1=1#............#Initial pressure in atm\n",
+    "cp=1.003#.........#Specifc heat at constant vpressure in kJ/kgK\n",
+    "t1=21#...........#Initial temperature in Celsius\n",
+    "t2=43#..........#Final temperature in Celsius\n",
+    "rp=1.35#.........#Pressure ratio\n",
+    "ga=1.4#.........#Ratio os specific heats\n",
+    "delt=3.3#.......#Change in temperature \n",
+    "cpw=4.18#.......#Specific heat for water in kJ/kgK\n",
+    "#Calculations\n",
+    "W=ma*cp*(t2-t1)#............#Work output in kJ\n",
+    "print \"Work output = %0.2f kW\"%W\n",
+    "t21=(t1+273)*(rp**((ga-1)/ga))#...........#Final temperature if the compression had been isentropic\n",
+    "Qr=ma*cp*(t21-(t2+273))#............#Heat rejected in kJ\n",
+    "mw=Qr/(cpw*delt)#........#Mass of cooling water in kg/min\n",
+    "print \"Mass of cooling water = %0.2f kg/min\"%mw"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.6 PAGE 754"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 2,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Swept volume = 0.03 m**3\n",
+      "Delivery temperature = 449.90 K\n",
+      "Indicated Power = 57.58 kW\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "ma=14#........#Quantity of air delivered in kg/min\n",
+    "p1=1.013#......#Intake pressure in bar\n",
+    "t1=288#.........#Intake temperature in K\n",
+    "p2=7#...........#Delivery pressure in bar\n",
+    "N=300#..........#Compressor rpm\n",
+    "pervc=0.05#.......#Percentage of clearance volume in the total stroke volume\n",
+    "n=1.3#............#Compressor and expansion index\n",
+    "#Calculations\n",
+    "V1byVs=pervc+1#\n",
+    "v1minv4=ma/(N*2)#\n",
+    "v4byv3=((p2/p1)**(1/n))#\n",
+    "v4byvs=v4byv3*pervc#\n",
+    "Vs=v1minv4/(V1byVs-v4byvs)#.....#Swept volume in m**3\n",
+    "print \"Swept volume = %0.2f m**3\"%Vs\n",
+    "t2=t1*((p2/p1)**((n-1)/n))#........#Delivery Temperature in K\n",
+    "print \"Delivery temperature = %0.2f K\"%t2\n",
+    "IP=((n)/(n-1))*p1*(10**5)*((ma)/(60*1000))*(((p2/p1)**((n-1)/n))-1)#\n",
+    "print \"Indicated Power = %0.2f kW\"%IP"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.7 PAGE 754"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 3,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Indicated power = 63.51 kW\n",
+      "Volumetric efficiency = 2.07 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "FAD=14#...........#Free air delivered in m**3/min\n",
+    "p1=0.95#.........#Induction pressure in bar\n",
+    "t1=305#........#Induction temperature in K\n",
+    "p2=7#...........#Delivery pressure in bar\n",
+    "n=1.3#...........#Adiabatic index\n",
+    "VcbyVs=0.05#........#Ratio of clearance volume and swept volume\n",
+    "R=287#...........#Gas constant in J/kgK\n",
+    "t=288#...........#free air temperature in K\n",
+    "p=1.013#.........#free air pressure in bar\n",
+    "#Calculations\n",
+    "m=(p*100000*FAD)/(R*t)#..........#Mass delivered per min in kg\n",
+    "t2=t1*((p2/p1)**((n-1)/n))#\n",
+    "IP=((n/(n-1))*m*(R/1000)*(t2-t1))/60#.........#Indicated power in kW\n",
+    "print \"Indicated power = %0.2f kW\"%IP\n",
+    "v4byv3=(p2/p1)**(1/n)#v4byvs=v4byv3*VcbyVs#v1minv4=(1+VcbyVs)-v4byvs#\n",
+    "Vbyvs=v1minv4*(t/t1)*(p1/p)#\n",
+    "etav=Vbyvs/1#.............#Volumetric efficiency\n",
+    "print \"Volumetric efficiency = %0.2f %%\"%(etav*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.8 PAGE 755"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 4,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Power input to compressor = 83.65 kW\n",
+      "Compressor stroke = 300.00 mm\n",
+      "Compressor bore = 291.43 mm\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "FAD=16#.......#Free air delivered in m**3/min\n",
+    "p1=0.96#......#Suction pressure in bar\n",
+    "t1=303#.......#Suction temperature in K\n",
+    "n=1.3#........#Compression index\n",
+    "k=0.04#........#Clearance ratio\n",
+    "p2=6#.........#Delivery pressure in bar\n",
+    "etamech=0.9#...#Mechanical efficiency\n",
+    "vp=300#.......#Piston speed in m/min\n",
+    "N=500#........#Compressor rpm\n",
+    "p=1#.....#Ambient pressure in bar\n",
+    "t=288#.....#Ambient temperature in K\n",
+    "etac=0.85#...#Compressor efficiency\n",
+    "R=0.287#......#Universal gas constant\n",
+    "#Calculations\n",
+    "m=(p*10**5*FAD)/(R*1000*t)#...........#Mass flow rate of compressor in kg/min\n",
+    "t2=t1*((p2/p1)**((n-1)/n))#.....#Temperature at the end of compression in K\n",
+    "P=(n/(n-1))*(m/60)*R*(t2-t1)*(1/etamech)*(1/etac)#..........#Power input to compressor in kW\n",
+    "print \"Power input to compressor = %0.2f kW\"%P\n",
+    "L=vp/(2*N)#.........#Stroke in m\n",
+    "print \"Compressor stroke = %0.2f mm\"%(L*1000)\n",
+    "etav=((t/t1)*(p1/p)*(1+k-(k*((p2/p1)**(1/n)))))#........#Volumetric efficiency\n",
+    "D=sqrt(FAD/((pi/4)*L*N*2*etav))#...........#Compressor bore in m\n",
+    "print \"Compressor bore = %0.2f mm\"%(D*1000)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.9 PAGE 756"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 5,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Volumetric efficiency = 91.10 %\n",
+      "Power required to drive the compressor = 2.27 kW\n",
+      "Compressor rpm :  486.0\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "m=0.6#..........#Mass of air delivered in kg/min\n",
+    "p2=6#.........#Delivery pressure in bar\n",
+    "p1=1#..........#Induction pressure in bar\n",
+    "t1=303#........#Induction temperature in K\n",
+    "D=0.1#.........#Compressor bore in m\n",
+    "L=0.15#........#Compressor stroke in m\n",
+    "k=0.03#........#Clearance ratio\n",
+    "etamech=0.85#....#Mechanical efficiency\n",
+    "R=0.287#.......#Gas constant in kJ/kgK\n",
+    "n=1.3#........#Compression index\n",
+    "#Calculations\n",
+    "etav=(1+k)-(k*((p2/p1)**(1/n)))#..........#Volumetric efficiency\n",
+    "print \"Volumetric efficiency = %0.2f %%\"%(etav*100)\n",
+    "IP=(n/(n-1))*(m/60)*R*t1*(((p2/p1)**((n-1)/n))-1)#.........#Indicated power in kW\n",
+    "P=IP/etamech#...........#Power required to drive the compressor in kW\n",
+    "print \"Power required to drive the compressor = %0.2f kW\"%P\n",
+    "FAD=(m*R*t1*1000)/(p1*10**5)#...........#Free air delivery in m**3/min\n",
+    "Vd=FAD/etav#........#Displacement volume in m**3/min\n",
+    "N=Vd/((pi/4)*D*D*L)#.........#Compressor rpm\n",
+    "print \"Compressor rpm : \",round(N)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.10 PAGE 756"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 6,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Percentage change in free air delivery = 2.68 %\n",
+      "Percentage change in power delivered = 2.68 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "L=88#...........#Compressor stroke in cm\n",
+    "k=0.02#...........#Clearance ratio\n",
+    "p3=8.2#...........#Delivery pressure in bar\n",
+    "p4=1.025#.......#Suction pressure in bar\n",
+    "p1=p4#.......#Suction pressure in bar \n",
+    "n=1.3#.........#Compression index\n",
+    "lo=0.55#...#Length of distance piece fitted after overhaul in cm\n",
+    "#Calculations\n",
+    "pcfa=(((L+(L*k))-((L*k)*((p3/p4)**(1/n))))-(((k*L)+lo+L)-(((k*L)+lo)*((p3/p4)**(1/n)))))/((L+L*k)-((L*k)*((p3/p4)**(1/n))))\n",
+    "print \"Percentage change in free air delivery = %0.2f %%\"%(pcfa*100)\n",
+    "pcpa=pcfa#......#Percentage change in power delivered\n",
+    "print \"Percentage change in power delivered = %0.2f %%\"%(pcpa*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.11 PAGE 757"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 7,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Motor power = 241.07 kW\n",
+      "Compressor bore = 262.71 mm\n",
+      "Compressor stroke = 315.25 mm\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "v=30#.............#Suction volume in m**3/min\n",
+    "p1=1#...........#Suction pressure in bar\n",
+    "t1=300#.........#Suction temperature in K\n",
+    "p2=16#...........#Delivery pressure in bar\n",
+    "N=320#..........#Compressor rpm\n",
+    "k=0.04#.........#Clearance ratio\n",
+    "rld=1.2#.........#Ratio of stroke to bore\n",
+    "etamech=0.82#....#Mechanical efficiency\n",
+    "n=1.32#.........#Compression index\n",
+    "ti=39+273#......#Temperature inside the suction chamber in K\n",
+    "nc=4#.........#No of cylineders\n",
+    "#Calculations\n",
+    "W=(n/(n-1))*(p1/1000)*10**5*(v/60)*(((p2/p1)**((n-1)/n))-1)#........#Work done in kW\n",
+    "mp=W/etamech#..........#Motor power in kW\n",
+    "print \"Motor power = %0.2f kW\"%mp\n",
+    "etav=((1+k)-(k*((p2/p1)**(1/n))))*(t1/ti)#........#Volumetric efficiency\n",
+    "Vs=(v/nc)*(1/(2*N))*(1/etav)#............#Swept volume of cylinder in m**3\n",
+    "D=(Vs/((pi/4)*rld))**(1/3)#.............#Compressor bore in m\n",
+    "L=D*rld#..............#Compresor stroke in m\n",
+    "print \"Compressor bore = %0.2f mm\"%(D*1000)\n",
+    "print \"Compressor stroke = %0.2f mm\"%(L*1000)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.12 PAGE 758"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 8,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Diameter of compressor cylinder = 159.70 mm\n",
+      "Stroke of compressor cylinder = 191.64 mm\n",
+      "Diameter of engine cylinder = 98.49 mm\n",
+      "Stroke of engine cylinder = 118.18 mm\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "n=2#........#No of cylinders \n",
+    "ma=16#........#Mass of air supplied per min in kg\n",
+    "p1=1#........#Suction pressure in bar\n",
+    "t1=288#.......#Suction temperature in K\n",
+    "k=0.04#.......#Clearance ratio\n",
+    "ni=1.3#........#Compression index\n",
+    "R=0.287#........#Gas constant in kJ/kgK\n",
+    "N=2000#........#Engine rpm\n",
+    "p3=7#...........#Delivery pressure in bar\n",
+    "rld=1.2#...........#Ratio of stroke to bore for compressor cylinder and engine cylinder\n",
+    "etamech=0.82#.........#Mechanical efficiency of engine\n",
+    "pmb=5.5#..........#Mean effective pressure in bar in engine\n",
+    "ne=4#.............#No of engine cylinders\n",
+    "#Calculations\n",
+    "Vs=(((ma/n)*R*1000*t1)/(p1*10**5*N))/((1+k)-(k*((p3/p1)**(1/ni))))#\n",
+    "Dc=(Vs/((pi/4)*rld))**(1/3)#.........#Diameter of compressor cylinder in m\n",
+    "Lc=rld*Dc#.............#Stroke of the compressor cylinder in m\n",
+    "print \"Diameter of compressor cylinder = %0.2f mm\"%(Dc*1000)\n",
+    "print \"Stroke of compressor cylinder = %0.2f mm\"%(Lc*1000)\n",
+    "IP=(ni/(ni-1))*(ma/60)*R*t1*(((p3/p1)**((ni-1)/ni))-1)#......#Indicated power of the compressor in kW\n",
+    "BP=IP/etamech#...............#Brake power of the engine in kW\n",
+    "De=((BP*60*1000)/(ne*pmb*10**5*rld*(pi/4)*N))**(1/3)#......#Diameter of the engine cylinder in m\n",
+    "Le=rld*De#...........#Stroke of the engine cylinder in m\n",
+    "print \"Diameter of engine cylinder = %0.2f mm\"%(De*1000)\n",
+    "print \"Stroke of engine cylinder = %0.2f mm\"%(Le*1000)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.13 PAGE 759"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 9,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Volumetric efficiency = 81.44 %\n",
+      "Diameter of the cylinder = 17.98 cm\n",
+      "Stroke of the cylinder = 17.98 cm\n",
+      "Brake power = 11.10 kW\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "nc=1.25#......#Index of compression\n",
+    "ne=1.3#......#Index of expansion\n",
+    "etamech=0.85#.......#Mechanical efficiency\n",
+    "p1=1#.........#Suction pressure in bar\n",
+    "p2=7.5#.......#Delivery pressure in bar\n",
+    "t1=25+273#....#Suction temperature in bar\n",
+    "Vamb=2.2#.....#Volume of free air delivered in m**3\n",
+    "N=310#........#Engine rpm\n",
+    "k=0.05#.......#Clearance ratio\n",
+    "pamb=1.03#.....#Ambient pressure in bar\n",
+    "tamb=293#......#Ambient temperature in K\n",
+    "#Calculations\n",
+    "etav=(1+k-(k*((p2/p1)**(1/ne))))#........#Volumetric efficiency\n",
+    "print \"Volumetric efficiency = %0.2f %%\"%(etav*100)\n",
+    "v1=(pamb*Vamb*t1)/(p1*tamb)#.......#Volume of air delivered at suction condition in m**3\n",
+    "vs=(v1/(etav*N*2))#.........#Swept volume in m**3\n",
+    "D=(vs/(pi/4))**(1/3)#........#Diameter of the cylinder in m\n",
+    "L=D#\n",
+    "print \"Diameter of the cylinder = %0.2f cm\"%(D*100)\n",
+    "print \"Stroke of the cylinder = %0.2f cm\"%(L*100)\n",
+    "W=2*vs*10**5*(((nc)/(nc-1))*p1*(1+k)*(((p2/p1)**((nc-1)/(nc)))-1)-((ne)/(ne-1))*p1*(k*((p2/p1)**(1/ne)))*(((p2/p1)**((ne-1)/(ne)))-1))#..........#Work done per cycle of operation in Nm/cycle\n",
+    "IP=W*N/(60*1000)#...............#Indicated power in kW\n",
+    "BP=IP/etamech#.............#Brake power in kW\n",
+    "print \"Brake power = %0.2f kW\"%BP"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.14 PAGE 760"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 10,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Compressor diameter = 35.75 cm\n",
+      "Compressor stroke = 53.63 cm\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "v=14#..........#Volume of air delivered in m**3\n",
+    "p1=1#........#Suction pressure in bar\n",
+    "p2=7#........#Delivery pressure in bar\n",
+    "N=310#........#Compressor rpm\n",
+    "n=1.35#........#Compression index\n",
+    "k=0.05#........#Clearance ratio\n",
+    "rld=1.5#.........#Ratio of cylinder length and diameter\n",
+    "#Calculations\n",
+    "etav=(1+k)-(k*((p2/p1)**(1/n)))#..........#Volumetric efficiency\n",
+    "Vs=v/(etav*N)#.............#Swept volume in m**3\n",
+    "D=((Vs)/((pi/4)*rld))**(1/3)#......#Compressor diameter in m\n",
+    "L=rld*D#......................#Compressor stroke in m\n",
+    "print \"Compressor diameter = %0.2f cm\"%(D*100)\n",
+    "print \"Compressor stroke = %0.2f cm\"%(L*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.15 PAGE 761"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 11,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Free air delivered = 13.89 m**3/min\n",
+      "Heat rejected during compression = 748.46 kJ/min\n",
+      "Power needed to drive the compressor = 52.01 kW\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "D=0.33#.........#Cylinder diameter in m\n",
+    "L=0.35#.........#Cylinder stroke in m\n",
+    "k=0.05#.........#Clearance ratio \n",
+    "N=300#..........#Compressor rpm\n",
+    "psuc=0.95#........#Suction pressure in bar\n",
+    "tsuc=298#.........#Suction temperature in K\n",
+    "pamb=1.013#......#Ambient pressure in bar\n",
+    "tamb=293#.........#Ambient temperature in K\n",
+    "p2=4.5#...........#Delivery pressure in bar\n",
+    "n=1.25#..........#Compression index\n",
+    "cv=0.717#...........#Specific heat at constant volume in kJ/kgK\n",
+    "ga=1.4#..........#Ratio of specific heats\n",
+    "etamech=0.8#......#Mechanical efficiency\n",
+    "R=0.287#.........#Gas constant in kJ/kgK\n",
+    "#Calculations\n",
+    "Vs=(pi/4)*D*D*L*N*2#............#Swept volume in m**3\n",
+    "p1=psuc#etav=1-(k*(((p2/p1)**(1/n))-1))#........#Volumetric efficiency\n",
+    "Vad=Vs*etav#................#Actual air drawn per min in m**3\n",
+    "FAD=(psuc/pamb)*(tamb/tsuc)*Vad#............#Free air delivered in m**3/min\n",
+    "print \"Free air delivered = %0.2f m**3/min\"%FAD\n",
+    "t1=tsuc#ma=(p1*10**5*Vad)/(R*1000*t1)#.......#Mass of air delivered per min in kg\n",
+    "t2=t1*((p2/p1)**((n-1)/n))#..........#Delivery temperature in K\n",
+    "Qr=ma*cv*((ga-n)/(n-1))*(t2-t1)#..........#Heat rejected during compression in kJ/min\n",
+    "print \"Heat rejected during compression = %0.2f kJ/min\"%Qr\n",
+    "P=((n)/(n-1))*R*t1*(ma/60)*(((p2/p1)**((n-1)/(n)))-1)*(1/etamech)#..........#Power needed to drive the compressor in kW\n",
+    "print \"Power needed to drive the compressor = %0.2f kW\"%P"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## Example 20.16 PAGE 762"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 12,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Power required to run the compressor = 4.19 kW\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "#Initialisation of variables\n",
+    "p1=1.03#...........#Intake pressure in bar\n",
+    "t1=300#............#Intake temperature in K\n",
+    "p2=7#.............#Intake pressure for High pressure cylinder in bar\n",
+    "t2=310#..............#Temperature of air entering high pressure cylinder in K\n",
+    "p3=40#............#Pressure of air after compression in bar\n",
+    "V=30#.........#volume of air delivered in m**3/h\n",
+    "R=0.287#............#Gas constant for air in kJ/kgK\n",
+    "ga=1.4#...........#Ratio of specific heats\n",
+    "#Calculations\n",
+    "m=p1*10**5*V/(R*1000*t1)#..........#Mass of air compressed in kg/h\n",
+    "t21=t1*((p2/p1)**((ga-1)/ga))#.......#Actual temperature of air entering high pressure cylinder in K\n",
+    "t3=t2*((p3/p2)**((ga-1)/ga))#........#Actual temperature of air after compression in K\n",
+    "W=((ga)/(ga-1))*m*(R/3600)*(t21-t1+t3-t2)#..........#Power required to run compressor in kW\n",
+    "print \"Power required to run the compressor = %0.2f kW\"%W"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.17 PAGE 762"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 13,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Diameter of low pressure cylinder = 267.30 mm\n",
+      "Diameter of high pressure cylinder = 109.13 mm\n",
+      "Power required to run the compressor = 57.49 kW\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "FAD=6#.......#Free air delivered in m**3/min\n",
+    "p1=1#........#suction pressure in bar\n",
+    "t1=300#......#Suction temperature in K\n",
+    "p3=40#.......#Delivery pressure in bar\n",
+    "p2=6#........#Intermediate pressure in bar\n",
+    "t3=300#........#Temperature at the inlet to 2nd stage in K\n",
+    "n=1.3#.........#Compression index\n",
+    "etamech=0.8#.....#Mechanical efficiency\n",
+    "N=400#............#Compressor rpm\n",
+    "R=0.287#.........#Gas constant in kJ/kgK\n",
+    "#Calculations  \n",
+    "dlp=(FAD/(N*(pi/4)))**(1/3)#...............#Diameter of the low pressure cylinder in m\n",
+    "dhp=sqrt(1/(dlp*N*(pi/4)))#............#Diameter of high pressure cylinder in m\n",
+    "print \"Diameter of low pressure cylinder = %0.2f mm\"%(dlp*1000)\n",
+    "print \"Diameter of high pressure cylinder = %0.2f mm\"%(dhp*1000)\n",
+    "m=(p1*FAD*10**5)/(R*t1*1000*60)#........#Mass flow of air in kg/s\n",
+    "W=n*(1/(n-1))*m*R*t1*(((p2/p1)**((n-1)/n))+((p3/p2)**((n-1)/n))-2)#........#Indicated work in kJ/s\n",
+    "P=W/etamech#...............#Power required in kW\n",
+    "print \"Power required to run the compressor = %0.2f kW\"%P"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.18 PAGE 763"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 14,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Intermediate pressure = 0.26 Mpa\n",
+      "Volume of low pressure cylinder = 0.02 m**3\n",
+      "Volume of high pressure cylinder = 0.01 m**3\n",
+      "Power required to drive the compressor = 42.96 kW\n",
+      "Heat rejected in the intercooler = 15.04 kW\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "ns=2#.............#No of stages\n",
+    "v1=0.2#.........#Intake volume in m**3/s\n",
+    "p1=1#..........#Intake pressure in bar\n",
+    "t1=289#...............#Intake temperature in K\n",
+    "p3=7#.........#Final pressure in bar\n",
+    "n=1.25#.......#Compression index\n",
+    "N=600#........#Compressor rpm\n",
+    "cp=1.005#.....#Specific heat at constant pressure in kJ/kgK\n",
+    "R=0.287#......#Gas constant in kJ/kgK\n",
+    "#Calculations\n",
+    "p2=sqrt(p1*p3)#......#Intermediate pressure in bar\n",
+    "print \"Intermediate pressure = %0.2f Mpa\"%(p2/10)\n",
+    "vslp=60*v1/N#..........#Volume of low pressure cylinder in m**3\n",
+    "vshp=p1*vslp/p2#..........#Volume of high pressure cylinder in m**3\n",
+    "print \"Volume of low pressure cylinder = %0.2f m**3\"%vslp\n",
+    "print \"Volume of high pressure cylinder = %0.2f m**3\"%vshp\n",
+    "W=(ns*(n/(n-1)))*p1*10**5*(v1/1000)*(((p3/p1)**((n-1)/(ns*n)))-1)#...........#Power required to drive the compressor in kW\n",
+    "print \"Power required to drive the compressor = %0.2f kW\"%W\n",
+    "m=p1*10**5*v1/(R*t1*1000)#.........#Mass of air handled in kg/s\n",
+    "t2=t1*((p2/p1)**((n-1)/n))#.........#Temperature at the end of first stage compression in K\n",
+    "Qr=m*cp*(t2-t1)#.......#Heat rejected in the intercooler in kW\n",
+    "print \"Heat rejected in the intercooler = %0.2f kW\"%Qr"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## Example 20.19 PAGE 764"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 15,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Ratio of cylinder diameters : 2.340\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "#initialisation of variables\n",
+    "p3=30#..........#delivery pressure in bar\n",
+    "p1=1#.........#suction pressure  in bar\n",
+    "t1=273+15#.......#suction temperature in K\n",
+    "n=1.3#.........#adiabatic index\n",
+    "#calculation\n",
+    "p2=sqrt(p1*p3)#.....#Pressure before entering High pressure cylinder in bar\n",
+    "t21=t1*((p2/p1)**((n-1)/n))#.........#Actual temperature before entering the high pressure turbine in K\n",
+    "r=sqrt((p2**(1/n))*(t21/t1))#............#Ratio of cylinder diameters\n",
+    "print \"Ratio of cylinder diameters : %0.3f\"%r"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.20 PAGE 765"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 16,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Work done in compressing 1 kg of gas = 388.53 kJ\n",
+      "Pressure in the intercooler would rise.\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "ns=2#.........#No of stages\n",
+    "p1=1#........#Suction pressure in bar\n",
+    "p2=7.4#.......#Intercooler pressure in bar\n",
+    "p3=42.6#.......#Delivery pressure in bar\n",
+    "t1=15+273#......#Suction temperature in K\n",
+    "n=1.3#........#Compression index\n",
+    "R=0.287#.......#Gas constant in kJ/kgK\n",
+    "dlp=0.09#.......#Diameter of low pressure cylinder in m\n",
+    "dhp=0.03#.......#Diameter of high pressure cylinder in m\n",
+    "etav=0.9#.....#Volumetric efficiency\n",
+    "#Calculations\n",
+    "W=n*(1/(n-1))*R*t1*(((p2/p1)**((n-1)/n))+((p3/p2)**((n-1)/n))-2)#\n",
+    "print \"Work done in compressing 1 kg of gas = %0.2f kJ\"%W\n",
+    "#Given that stroke length is same in both cases\n",
+    "rV=p2/p1#.........#Ratio of volumes\n",
+    "rECV=((dlp/dhp)**2)*etav#.........#Ratio of effective cylinder volumes\n",
+    "if (rECV>rV):\n",
+    "    print \"Pressure in the intercooler would rise.\"\n",
+    "elif (rECV<rV):\n",
+    "    print \"Pressure in the intercooler would fall\"\n",
+    "    "
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.21 PAGE 765"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 17,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Stroke length = 0.36 m\n",
+      "Bore = 0.27 m\n",
+      "Work required = 49.20 kW\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "V=4#...........#Volume of air handled in m**3/min\n",
+    "p1=1.016#.....#Suction pressure in bar\n",
+    "t1=288#........#Suction temperature in K\n",
+    "N=250#.........#Compressor rpm\n",
+    "p3=78.65#.....#Delivery pressure in bar\n",
+    "vp=3#........#Piston speed in m/s\n",
+    "etamech=0.75#.....#mechanical efficiency\n",
+    "etav=0.8#........#Volumetric efficiency\n",
+    "n=1.25#..........#Compression index\n",
+    "R=287#...........#Gas constant in J/kgK\n",
+    "ns=2#............#No of stages\n",
+    "#Calculations\n",
+    "l=(vp*60)/(2*N)#..........#Stroke length in m\n",
+    "d=sqrt(V/((pi/4)*l*N*etav))#.......#Bore in m\n",
+    "print \"Stroke length = %0.2f m\"%l\n",
+    "print \"Bore = %0.2f m\"%d\n",
+    "m=(p1*10**5*V)/(R*t1)#.......#Mass of air handled by the compressor in kg/min\n",
+    "p2=sqrt(p1*p3)#.............#Intermediate pressure in bar\n",
+    "t2=t1*((p2/p1)**((n-1)/n))#.........#Temperature at the end of first stage compression in K\n",
+    "W=ns*(n/(n-1))*(m/60)*(R/1000)*(t2-t1)*(1/etamech)#..........#Work required in kW\n",
+    "print \"Work required = %0.2f kW\"%W"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.22 PAGE 766"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 18,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Indicated power = 15.48 kW\n",
+      "Swept volume for low pressure cylinder = 0.0131 m**3\n",
+      "Swept volume of high pressure cylinder = 0.0044 m**3\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "m=4.5#.........#Amount of air compressed in kg/min\n",
+    "ps=1.013#.......#Suction pressure in bar\n",
+    "ts=288#.........#Suction temperature in K\n",
+    "rp=9#...........#Pressure ratio\n",
+    "n=1.3#.........#Compression index\n",
+    "k=0.05#........#Clearance ratio\n",
+    "N=300#.........#Compressor rpm\n",
+    "R=287#.........#Gas constant in J/kgK\n",
+    "ns=2#............#No of stages\n",
+    "#Calculations\n",
+    "ti=round(ts*((sqrt(rp))**((n-1)/n)))#......#Intermediate temperature in K\n",
+    "W=round(ns*n*(1/(n-1))*m*(R/1000)*(ti-ts))#..........#Work required per min in kJ\n",
+    "IP=W/60#.........#Indicated power in kW\n",
+    "print \"Indicated power = %0.2f kW\"%IP\n",
+    "mc=m/N#...........#Mass induced per cycle in kg\n",
+    "etav=(1+k)-(k*(sqrt(rp)**(1/n)))#.......#Volumetric efficiency\n",
+    "Vs=(mc*R*ts)/(ps*10**5*etav)#........#Swept volume for low pressure cylinder in m**3\n",
+    "print \"Swept volume for low pressure cylinder = %0.4f m**3\"%Vs\n",
+    "vdhp=(mc*ts*R)/(sqrt(rp)*ps*10**5)#............#Volume of air drawn in high pressure cylinder per cycle in m**3\n",
+    "vshp=vdhp/etav#...............#Swept volume ofhigh pressure cylinder in m**3\n",
+    "print \"Swept volume of high pressure cylinder = %0.4f m**3\"%vshp"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.23 PAGE 767"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 19,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Power required to run the compressor = 18.68 kW\n",
+      "Bore of low pressure cylinder = 19.06 cm\n",
+      "Stroke of low pressure cylinder = 19.06 cm\n",
+      "Bore of high pressure cylinder = 7.00 cm\n",
+      "Stroke of high pressure cylinder = 19.06 cm\n",
+      "Ratio of cylinder volumes : 7.4162\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "v1=2.2#...........#free air delivered by the compressor in m**3/min\n",
+    "p1=1#........#Suction pressure in bar\n",
+    "t1=298#.......#Suction temperature in K\n",
+    "pd=55#........#Delivery pressure in bar\n",
+    "N=210#.......#Compressor rpm\n",
+    "n=1.3#........#Compression index\n",
+    "k=0.05#.......#Clearance ratio for high pressure and low pressure cylinders\n",
+    "R=287#.......#Gas constant in J/kgK\n",
+    "ns=2#.......#No of stages\n",
+    "#Calculations\n",
+    "ps=p1#\n",
+    "m =(p1*v1*10**5)/(R*t1)#.........#Mass of air deivered in m**3/min\n",
+    "W=(ns*(n/(n-1)))*m*R*t1*(((pd/ps)**((n-1)/(ns*n)))-1)#...........#Work done by compressor in Nm/min\n",
+    "P=W/(60*1000)#...........#Power required to run the compressor\n",
+    "print \"Power required to run the compressor = %0.2f kW\"%P\n",
+    "pi=sqrt(ps*pd)#........#Intermediate pressure in bar\n",
+    "etav1=(1+k)-(k*((pi/p1)**(1/n)))#...........#Volumetric efficiency of the low pressure cylinder \n",
+    "Vs=(v1*10**6)/(etav1*N)#............#Swept volume in cm**3\n",
+    "dlp=(Vs/((pi/4)))**(1/3)#..........#Diameter of low pressure cylinder in cm\n",
+    "llp=dlp#.................#Stroke of low pressure cylinder in cm\n",
+    "print \"Bore of low pressure cylinder = %0.2f cm\"%dlp\n",
+    "print \"Stroke of low pressure cylinder = %0.2f cm\"%llp\n",
+    "dhp=sqrt(dlp*dlp/pi)#.........#Diameter of high pressure cylinder in cm\n",
+    "lhp=llp#\n",
+    "print \"Bore of high pressure cylinder = %0.2f cm\"%dhp\n",
+    "print \"Stroke of high pressure cylinder = %0.2f cm\"%lhp\n",
+    "rcv=pi/ps#.....#Ratio of cylinder volumes\n",
+    "print \"Ratio of cylinder volumes : %0.4f\"%rcv"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.24 PAGE 768"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 20,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Heat rejected to the intercooler = 2179.62 kJ/min\n",
+      "Diameter of high pressure cylinder = 184.68 mm\n",
+      "Power required for high pressure cylinder = 45.02 kW\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "p1=1#........#Suction pressure in bar\n",
+    "p2=4#.....#Intermediate pressure in bar\n",
+    "p5=3.8#.......#Pressure of air leaving the interooler in bar\n",
+    "p6=15.2#........#Delivery pressure in bar\n",
+    "t1=300#..........#Suction temperature in K\n",
+    "dlp=0.36#........#Diameter of low pressure cylinder in m\n",
+    "llp=0.4#........#Stroke of low pressure cylinder in m\n",
+    "N=220#........#Compressor rpm\n",
+    "k=0.04#........#Clearance ratio\n",
+    "cp=1.0035#.........#Specific heat at constant pressure in kJ/kgK\n",
+    "n=1.3#........#Compression index\n",
+    "R=0.287#........#Gas constant in kJ/kgK\n",
+    "p8=p5#\n",
+    "p3=p2#\n",
+    "p7=p6#\n",
+    "t5=t1#\n",
+    "#Calculations\n",
+    "Vslp=(pi/4)*dlp*dlp*llp*N*2#.......#Swept volume in m**3\n",
+    "etavlp=(1+k)-(k*((p2/p1)**(1/n)))#.....#Volumetric efficiency\n",
+    "valp=Vslp*etavlp#................#Volume of air drawn in low pressure cylinder in m**3\n",
+    "m=(p1*10**5*valp)/(R*1000*t1)#........#Mass of air drawin in kg/min\n",
+    "t2=round(t1*((p2/p1)**((n-1)/n)))#\n",
+    "Qr=m*cp*(t2-t5)#........#Heat rejected to the intercooler in kJ/min\n",
+    "print \"Heat rejected to the intercooler = %0.2f kJ/min\"%Qr\n",
+    "vahp=(m*R*t5*1000)/(p5*10**5)#...#Volume of air drawn into high pressure cylinder per min in m**3\n",
+    "Vshp=vahp/etavlp#.........#Swept volume of high pressure cylinder in m**3/min\n",
+    "dhp=sqrt(Vshp/((pi/4)*2*N*llp))#..........#Diameter of high pressure cylinder in m\n",
+    "print \"Diameter of high pressure cylinder = %0.2f mm\"%(dhp*1000)\n",
+    "P=(n/(n-1))*m*(1/60)*R*(t2-t1)#.......#Power required for high pressure cylinder in kW\n",
+    "print \"Power required for high pressure cylinder = %0.2f kW\"%P"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.25 PAGE 769"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 21,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Power required to run the compressor = 85.38 kW\n",
+      "Heat rejected in intercooler = 1742.36 kJ/min\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "ps=1#........#Suction pressure in bar\n",
+    "pi=4.2#.....#Intermediate pressure in bar\n",
+    "pi1=4#.......#Pressure of air leaving the interooler in bar\n",
+    "pd=18#........#Delivery pressure in bar\n",
+    "t1=298#..........#Suction temperature in K\n",
+    "t5=t1#\n",
+    "dlp=0.4#........#Diameter of low pressure cylinder in m\n",
+    "llp=0.5#........#Stroke of low pressure cylinder in m\n",
+    "N=200#........#Compressor rpm\n",
+    "k=0.05#........#Clearance ratio\n",
+    "cp=1.004#.........#Specific heat at constant pressure in kJ/kgK\n",
+    "n=1.25#........#Compression index\n",
+    "R=0.287#........#Gas constant in kJ/kgK\n",
+    "#Calculations\n",
+    "Vslp=(pi/4)*dlp*dlp*llp#..........#Swept volume of low pressure cylinder in m**3\n",
+    "etavlp=(1+k)-(k*((pi/ps)**(1/n)))#.....#Volumetric efficiency\n",
+    "t2=round(t1*((pi/ps)**((n-1)/n)))#\n",
+    "m=(ps*10**5*etavlp*Vslp)/(R*1000*t1)#...#Mass of air in kg\n",
+    "wlp=((n)/(n-1))*R*1000*t1*m*(((pi/ps)**((n-1)/(n)))-1)#..........#Work done per min in Nm in low pressure cylinder\n",
+    "whp=((n)/(n-1))*R*t5*m*1000*(((pd/pi1)**((n-1)/(n)))-1)#..........#Work done per min in Nm in high pressure cylinder\n",
+    "W=wlp+whp#.........#Net work done in Nm\n",
+    "IP=(W*N)/(60*1000)#............#Power required to run the compressor in kW\n",
+    "print \"Power required to run the compressor = %0.2f kW\"%IP\n",
+    "Qr=m*N*cp*(t2-t1)#...........#Heat rejected in intercooler in kJ/min\n",
+    "print \"Heat rejected in intercooler = %0.2f kJ/min\"%Qr"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.26 PAGE 771"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 22,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Power required = 49.23 kW\n",
+      "Isothermal work done = 41.78 kW\n",
+      "Isothermal efficiency = 84.86 %\n",
+      "Free air delivered = 9.04 m**3/min\n",
+      "Heat transferred in intercooler = 19.89 kW\n",
+      "\n",
+      "Swept volume for low pressure stage = 0.02 m**3\n",
+      "\n",
+      "\n",
+      "Clearance volume for low pressure stage = 8.90e-04 m**3\n",
+      "\n",
+      "\n",
+      "Swept volume for high pressure stage = 0.01 m**3\n",
+      "\n",
+      "\n",
+      "Clearance volume for high pressure stage = 3.48e-04 m**3\n",
+      "\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt,log\n",
+    "# Initialisation of Variables\n",
+    "p1=1#............#Intake pressure in bar\n",
+    "p2=4#..............#Pressure after first stage in bar\n",
+    "p3=16#............#Final pressure in bar\n",
+    "ns=2#............#No of stages\n",
+    "t1=300#............#Intake temperature in K\n",
+    "n=1.3#............#Compression index\n",
+    "klp=0.04#.........#Clearance ratio for low pressure cylinder\n",
+    "khp=0.06#........#Clearance ratio for high pressure cylinder\n",
+    "N=440#............#Engine rpm\n",
+    "R=0.287#..........#Gas constant in kJ/kgK\n",
+    "m=10.5#.............#Mass of air delivered in kg/min\n",
+    "cp=1.005#.........#Specific heat at constant pressure in kJ/kgK\n",
+    "#Calculations\n",
+    "rp=sqrt(p1*p3)#...........#Pressure ratio per stage\n",
+    "P=((ns*n)/(n-1))*R*t1*(m/60)*(((p3/p1)**((n-1)/(ns*n)))-1)#..........#Work done per min in Nm\n",
+    "print \"Power required = %0.2f kW\"%P\n",
+    "isoWd=(m/60)*R*t1*log(p3/p1)#..........#Isothermal work done in Nm\n",
+    "print \"Isothermal work done = %0.2f kW\"%isoWd\n",
+    "etaiso=isoWd/P#...............#Isothermal efficiency\n",
+    "print \"Isothermal efficiency = %0.2f %%\"%(etaiso*100)\n",
+    "FAD=(m*R*t1*1000)/(p1*10**5)#.............#Free air delivered in m**3/min\n",
+    "print \"Free air delivered = %0.2f m**3/min\"%FAD\n",
+    "t2=t1*((p2/p1)**((n-1)/n))#.....#Temperature at the end of compression in K\n",
+    "Qt=(m/60)*cp*(t2-t1)#..............#Heat transferred in intercooler in kW\n",
+    "print \"Heat transferred in intercooler = %0.2f kW\"%Qt\n",
+    "etavlp=(1+klp)-(klp*((p2/p1)**(1/n)))#..........#Volumetric efficiency of low pressure stage\n",
+    "etavhp=(1+khp)-(khp*((p2/p1)**(1/n)))#..........#Volumetric efficiency of high pressure stage\n",
+    "vslp=FAD/(N*etavlp)#......#Swept volume for low pressure stage in m**3\n",
+    "vclp=klp*vslp#..............#Clearance volume for low pressure stage in m**3\n",
+    "print \"\\nSwept volume for low pressure stage = %0.2f m**3\\n\"%(vslp)\n",
+    "print \"\\nClearance volume for low pressure stage = %0.2e m**3\\n\"%(vclp)\n",
+    "vshp=FAD/(N*rp*etavhp)#......#Swept volume for high pressure stage in m**3\n",
+    "vchp=khp*vshp#..............#Clearance volume for high pressure stage in m**3\n",
+    "print \"\\nSwept volume for high pressure stage = %0.2f m**3\\n\"%(vshp)\n",
+    "print \"\\nClearance volume for high pressure stage = %0.2e m**3\\n\"%(vchp)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.27 PAGE 771"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 23,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Work done = 1297727.20 Nm\n",
+      "Isothermal work done = 1146628.13 Nm\n",
+      "Isothermal efficiency = 88.36 %\n",
+      "Single stage work done per min = 1686780.23 Nm\n",
+      "Percentage of work saved : 23.06 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "ns=3#......#No of stages\n",
+    "p1=1.05#......#Intake pressure in bar\n",
+    "pd=40#..........#Delivery pressure in bar\n",
+    "V=3#..........#Volume of air xupplied per min in m**3\n",
+    "n=1.25#........#Compression index\n",
+    "#Calculations\n",
+    "Wd=((ns*n)/(n-1))*p1*V*10**5*(((pd/p1)**((n-1)/(ns*n)))-1)#..........#Work done per min in Nm\n",
+    "print \"Work done = %0.2f Nm\"%Wd\n",
+    "isoWd=10**5*p1*V*log(pd/p1)#..........#Isothermal work done in Nm\n",
+    "print \"Isothermal work done = %0.2f Nm\"%isoWd\n",
+    "etaiso=isoWd/Wd#...............#Isothermal efficiency\n",
+    "print \"Isothermal efficiency = %0.2f %%\"%(etaiso*100)\n",
+    "wdss=((n)/(n-1))*p1*V*10**5*(((pd/p1)**((n-1)/(n)))-1)#..........#Single stage Work done per min in Nm\n",
+    "print \"Single stage work done per min = %0.2f Nm\"%wdss\n",
+    "perws=(wdss-Wd)/wdss#.......#Percentage of work saved\n",
+    "print \"Percentage of work saved : %0.2f %%\"%(perws*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.28 PAGE 772"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 24,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "\n",
+      "\n",
+      "Intermediate pressures: \n",
+      "  p2 = 3.30\n",
+      "  p3 = 10.90\n",
+      "\n",
+      "Indicated power required = 101.19 kW\n"
+     ]
+    }
+   ],
+   "source": [
+    "# Initialisation of Variables\n",
+    "p1=1#.............#Intake pressure in bar\n",
+    "p4=36#........#Final pressure in bar\n",
+    "n=1.25#.........#Compression index\n",
+    "R=0.287#.......#Gas constant in kJ/kgK\n",
+    "t1=300#..........#Intake temperature in K\n",
+    "ns=3#...........#No of stages\n",
+    "v=15#..........#Volume of air delivered in m**3\n",
+    "#Calculations\n",
+    "p2=p1*((p4/p1)**(1/ns))#\n",
+    "p3=p2*((p4/p1)**(1/ns))#\n",
+    "print \"\\n\\nIntermediate pressures: \\n  p2 = %0.2f\\n  p3 = %.2f\\n\"%(p2,p3)\n",
+    "t2=t1*((p4/p1)**(((n-1)/n)*(1/ns)))#....#Delivery temperature  in K\n",
+    "m=p1*10**5*v/(R*1000*t1)#...........#Mass of air handled per min in kg\n",
+    "Wt=((n/(n-1))*m*R*(1/60)*(t2-t1)*ns)#........#Total work done in three stages \n",
+    "print \"Indicated power required = %0.2f kW\"%Wt"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.29 PAGE 772"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 25,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Heat rejected in intercooler after first stage = 1276.59 kJ/min\n",
+      "Heat rejected in intercooler after second stage = 1639.45 kJ/min\n",
+      "Heat rejected in intercooler after third stage = 1875.18 kJ/min\n",
+      "Diameter of the intermediate cylinder = 179.48 mm\n",
+      "Diameter of the intermediate cylinder = 87.59 mm\n",
+      "Shaft power = 142.68 kW\n",
+      "\n",
+      "Heat transferred during first stage = 455.70 kJ/min\n",
+      "\n",
+      "Heat transferred during second stage = 438.71 kJ/min\n",
+      "\n",
+      "Heat transferred during third stage = 334.22 kJ/min\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "ns=3#........#No of stages\n",
+    "N=200#.......#Compressor rpm\n",
+    "p1=1#.......#Intake pressure in bar\n",
+    "t1=20+273#....#Intake temperature in K\n",
+    "D=0.35#......#Engine bore in m\n",
+    "L=0.4#.......#Engine stroke in m\n",
+    "p2=4#........#Discharge pressure from first stage in bar\n",
+    "p6=16#........#Discharge pressure from second stage in bar\n",
+    "p10=64#........#Discharge pressure from third stage in bar\n",
+    "pd=0.2#........#Loss of pressure between intercoolers in bar\n",
+    "R=0.287#......#Gas constant in kJ/kgK\n",
+    "k=0.04#.......#Clearence volume in 4% of the stroke volume\n",
+    "n1=1.2#.....#Compressor index for first stage\n",
+    "n2=1.25#.....#Compressor index for second stage\n",
+    "n3=1.3#.....#Compressor index for third stage\n",
+    "cp=1.005#......#Specific heat at constant pressure in kJ/kgK\n",
+    "etamech=0.8#.....#Mechanical efficiency\n",
+    "#Calculations\n",
+    "p5=p2-pd#\n",
+    "p9=p6-pd#\n",
+    "t5=t1#\n",
+    "t9=t1#\n",
+    "Vs=(pi/4)*D*D*L*N*2#............#Swept volume of low pressure cylinder per min in m**3\n",
+    "etav1=(1+k)-(k*((p2/p1)**(1/n1)))#.....#Volumetric efficiency in first stage\n",
+    "etav2=(1+k)-(k*((p6/p5)**(1/n2)))#.....#Volumetric efficiency in second stage\n",
+    "etav3=(1+k)-(k*((p10/p9)**(1/n3)))#.....#Volumetric efficiency in third stage\n",
+    "vain1=Vs*etav1#.................#Volume of air taken in first stage in m**3/min\n",
+    "m=(p1*10**5)*vain1/(R*t1*1000)#...........#Mass of air intake in kg/min in first stage\n",
+    "t2=round(t1*((p2/p1)**((n1-1)/n1)))#\n",
+    "t6=t5*((p6/p5)**((n2-1)/n2))#\n",
+    "t10=t9*((p10/p9)**((n3-1)/n3))#\n",
+    "Qr1=m*cp*(t2-t5)#........#Heat rejected in intercooler after first stage in kJ/min\n",
+    "Qr2=m*cp*(t6-t9)#........#Heat rejected in intercooler after second stage in kJ/min\n",
+    "Qr3=m*cp*(t10-t1)#........#Heat rejected in intercooler after third stage in kJ/min\n",
+    "print \"Heat rejected in intercooler after first stage = %0.2f kJ/min\"%Qr1\n",
+    "print \"Heat rejected in intercooler after second stage = %0.2f kJ/min\"%Qr2\n",
+    "print \"Heat rejected in intercooler after third stage = %0.2f kJ/min\"%Qr3\n",
+    "vainip=m*R*t5*1000/(p5*10**5)#.........#Volume drawn in intermediate pressure cylinder/min\n",
+    "Vsip=vainip/etav2#.............#Swept volume of intermediate cylinder in m**3/min\n",
+    "Dip=sqrt(Vsip/(2*N*L*(pi/4)))#............#Diameter of the intermediate cylinder in m\n",
+    "print \"Diameter of the intermediate cylinder = %0.2f mm\"%(Dip*1000)\n",
+    "vainhp=m*R*t9*1000/(p9*10**5)#.........#Volume drawn in high pressure cylinder/min\n",
+    "Vshp=vainhp/etav3#.............#Swept volume of high pressure cylinder in m**3/min\n",
+    "Dhp=sqrt(Vshp/(2*N*L*(pi/4)))#............#Diameter of the intermediate cylinder in m\n",
+    "print \"Diameter of the intermediate cylinder = %0.2f mm\"%(Dhp*1000)\n",
+    "Ps=(((n1/(n1-1))*m*R*(t2-t1))+((n2/(n2-1))*m*R*(t6-t5))+((n3/(n3-1))*m*R*(t10-t9)))*(1/(60*etamech))#...#Shaft power in kW\n",
+    "print \"Shaft power = %0.2f kW\"%Ps\n",
+    "cv=cp-R#..........#Specific heat at constant volume in kJ/kgK\n",
+    "ga=cp/cv#...........#Ratio of specific heats\n",
+    "Qt1=cv*((ga-n1)/(ga-1))*(t2-t1)*m#............#Heat transfer during first stage in kJ/min\n",
+    "Qt2=cv*((ga-n2)/(ga-1))*(t6-t1)*m#............#Heat transfer during second stage in kJ/min\n",
+    "Qt3=cv*((ga-n3)/(ga-1))*(t10-t1)*m#............#Heat transfer during third stage in kJ/min\n",
+    "print\"\\nHeat transferred during first stage = %0.2f kJ/min\"%(Qt1)\n",
+    "print \"\\nHeat transferred during second stage = %0.2f kJ/min\"%(Qt2)\n",
+    "print \"\\nHeat transferred during third stage = %0.2f kJ/min\"%(Qt3)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.30 PAGE 773"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 26,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "No of stages : 4\n",
+      "Exact stage pressure ratio : 3.34\n",
+      "\n",
+      "Intermediate pressures\n",
+      "p4=37.38\n",
+      "p3=10.90\n",
+      "p2=4.00\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "p1=1#.....#Intake pressure in bar\n",
+    "p5=125#.....#Pressure of the compressed air in bar\n",
+    "rpr=4#.........#Pressure ratio is restricted to 4\n",
+    "#Calculations\n",
+    "X=(log(p5/p1)/log(rpr))#\n",
+    "if(X>round(X)):\n",
+    "    x=round(X)+1#\n",
+    "else:\n",
+    "    x=round(X)#\n",
+    "print \"No of stages : %d\"%x\n",
+    "esrp=(p5/p1)**(1/x)#\n",
+    "print \"Exact stage pressure ratio : %0.2f\"%esrp\n",
+    "p4=p5/esrp#p3=p4/esrp#p2=p3/esrp#......#Intermediate pressures in bar\n",
+    "print \"\\nIntermediate pressures\\np4=%.2f\\np3=%.2f\\np2=%.2f\"%(p4,p3,p2)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.31 PAGE 774"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 27,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "No of stages: 4\n",
+      "Total work done = 512.24 kJ/kg\n",
+      "Heat rejected in intercoolers = 254.23 kJ/kg\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "ps=1#.........#Suction pressure in bar\n",
+    "t1=273+125#.......#Delivery temperature in K\n",
+    "pd=160#...........#Delivery pressure in bar\n",
+    "tm=40+273#........#Min temperature\n",
+    "ts=298#........#Suction temperature in K\n",
+    "n=1.25#......#Adiabatic index\n",
+    "cv=0.71#.......#Specific heat at constant volume in kJ/kgK\n",
+    "R=0.287#......#Gas constant in kJ/kgK\n",
+    "ns=3#.......#No of stages\n",
+    "#Calculations\n",
+    "p1=ps*((t1/ts)**(n/(n-1)))#\n",
+    "x=(log(pd/p1))/(((n/(n-1))*(log(t1/tm))))#\n",
+    "print \"No of stages: %d\"%(round(x)+1)\n",
+    "rp1=p1#...........#Pressure ratio in 1st stage\n",
+    "rp=(pd/rp1)**(1/ns)#.........#Pressure ratio in the following stage\n",
+    "W=(n/(n-1))*R*ts*(((rp1)**((n-1)/n))-1)#.........#Work done in first stage in kJ\n",
+    "Wf=ns*(n/(n-1))*R*tm*(((rp)**((n-1)/n))-1)#.........#Work done in next three stages in kJ\n",
+    "wt=W+Wf#............#Total work done per kg in kJ\n",
+    "print \"Total work done = %0.2f kJ/kg\"%wt\n",
+    "cp=cv+R#..............#Specific heat at constant pressure in kJ/kgK\n",
+    "Qr=ns*cp*(t1-tm)#.............#Heat rejected in intercoolers in kJ/kg\n",
+    "print \"Heat rejected in intercoolers = %0.2f kJ/kg\"%Qr"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.32 PAGE 775"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 28,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Swept capacity of low pressure cylinder = 0.12 m**3\n",
+      "Swept capacity of intermediate pressure cylinder = 0.03 m**3\n",
+      "Swept capacity of intermediate pressure cylinder = 0.01 m**3\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "Vamb=10.5#........#Free air volume in m**3\n",
+    "Pamb=1.013#...........#Free air presssure in bar\n",
+    "Tamb=273+15#..........#Free air temperature in K\n",
+    "T1=(273+25)#...........#Temperature at the end of suction in all cylinders in K\n",
+    "P1=1#............#Pressure at the suction in bar\n",
+    "pd=95#...........#Delivery presssure in bar\n",
+    "N=100#.........#Compressor rpm\n",
+    "n=1.25#..........#Adiabatic index\n",
+    "k=0.04#.........#Fractional clearances for LP\n",
+    "k1=0.07#.........#Fractional clearances for HP\n",
+    "#Calculations\n",
+    "z=(pd/P1)**(1/3)#.........#Pressure ratio\n",
+    "pi1=z*P1#\n",
+    "pi2=z*pi1#\n",
+    "etavollp=1+k-(k*(z**(1/n)))#\n",
+    "etavolhp=1+k1-(k1*(z**(1/n)))#\n",
+    "v1=(Pamb*Vamb*T1)/(Tamb*P1)#\n",
+    "sclp=(round(v1))/(etavollp*N)#.........#Swept capacity of LP cylinder in m**3\n",
+    "print \"Swept capacity of low pressure cylinder = %0.2f m**3\"%sclp\n",
+    "vip=(Pamb*Vamb*T1)/(pi1*Tamb)#.........#Volume of free air reduced to suction conditions of IP cylinder\n",
+    "scip=vip/(etavolhp*N)#.........#Swept capacity of IP cylinder in m**3\n",
+    "print \"Swept capacity of intermediate pressure cylinder = %0.2f m**3\"%scip\n",
+    "vhp=(Pamb*Vamb*T1)/(pi2*Tamb)#.........#Volume of free air reduced to suction conditions of HP cylinder\n",
+    "schp=vhp/(etavolhp*N)#.........#Swept capacity of HP cylinder in m**3\n",
+    "print \"Swept capacity of intermediate pressure cylinder = %0.2f m**3\"%schp"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.34 PAGE 776"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 29,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Temperature at the end of expansion = 244.63 K\n",
+      "Indicated power of the motor = 0.75 kW\n",
+      "Mass of air supplied per min = 0.42 kg\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "D=0.0635#.......#Engine bore in m\n",
+    "L=0.114#.........#Engine stroke in m\n",
+    "p1=6.3#..........#Supply pressure in bar\n",
+    "t1=273+24#.........#Supply temperature in K\n",
+    "p4=1.013#..........#Exhaust pressure in bar\n",
+    "cv=0.05#............#Clearance volume is 5% of the swept volume\n",
+    "cr=0.5#..........#Cut off ratio\n",
+    "n=1.3#...........#Adiabatic index\n",
+    "R=287#...............#gas constant in kJ/kgK\n",
+    "N=300#.............#Engine rpm\n",
+    "ga=1.4#...........#Ratio of specific heats\n",
+    "#Calculations\n",
+    "Vs=(pi*D*D*L)/4#........#Swept volume in m**3\n",
+    "Vc=cv*Vs#..........#Clearance volume in m**3\n",
+    "v6=Vc#\n",
+    "v5=v6#\n",
+    "v1=(Vs/2)+Vc#\n",
+    "v2=Vs+Vc#\n",
+    "v3=v2#\n",
+    "p3=p4#\n",
+    "v4=v5+(cv*Vs)#\n",
+    "p2=p1*((v1/v2)**n)#.......#Pressure at the end of expansion\n",
+    "t2=t1*((v1/v2)**(n-1))#........#Temperature at the end of expansion in K\n",
+    "print \"Temperature at the end of expansion = %0.2f K\"%t2\n",
+    "p5=p4*((v4/v5)**n)#\n",
+    "w=((p1*(v1-v6))+(((p1*v1)-(p2*v2))/(n-1))-(p3*(v3-v4))-(((p5*v5)-(p4*v4))/(n-1)))*10**5#.......#Workk done per cycle in Nm\n",
+    "IP=(w*N)/(60*1000)#..........#Indicated power in kW\n",
+    "print \"Indicated power of the motor = %0.2f kW\"%IP\n",
+    "t3=t2*((p3/p2)**((ga-1)/ga))#\n",
+    "t4=t3#\n",
+    "m4=(p4*v4*10**5)/(R*t4)#\n",
+    "m1=(p1*v1*10**5)/(R*t1)#\n",
+    "ma=(m1-m4)*N#..........#Mass of air supplied per min\n",
+    "print \"Mass of air supplied per min = %0.2f kg\"%ma"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.35 PAGE 777"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 30,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Work input for roots compressor = 1.52 kJ/rev\n",
+      "Work input for vane compressor = 1.35 kJ/rev\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "v=0.03#..............#Induced volume in m**3/rev\n",
+    "p1=1.013#...........#Inlet pressure in bar\n",
+    "rp=1.5#............#Pressure ratio\n",
+    "ga=1.4#...........#Ratio of specific heats\n",
+    "#Calculations\n",
+    "p2=rp*p1#\n",
+    "wr=(p2-p1)*(10**5)*v/1000#.....#Work input for roots compressor in kJ\n",
+    "print \"Work input for roots compressor = %0.2f kJ/rev\"%wr\n",
+    "pi=(p2+p1)/2#\n",
+    "wv=((p2-pi)*(10**5)*v*((p1/pi)**(1/ga))*(1/1000))+((ga/(ga-1))*p1*(10**5)*(v/1000)*(((pi/p1)**((ga-1)/ga))-1))#...#Work input required for vane type in kJ/rev\n",
+    "print \"Work input for vane compressor = %0.2f kJ/rev\"%wv"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.36 PAGE 778"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 31,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Compressor efficiency = 85.98 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "v=0.08#.........#Volume of air compressed in m**3\n",
+    "p1=1#..........#Intake pressure in bar\n",
+    "p2=1.5#........#Pressure after compression in in bar\n",
+    "ga=1.4#.........#Ratio of specific heats\n",
+    "#Calculations\n",
+    "wac=v*(p2-p1)*10**5#........#Actual work done in Nm\n",
+    "wid=(ga/(ga-1))*p1*v*(10**5)*(((p2/p1)**((ga-1)/ga))-1)#...........#Ideal work done per revolution in Nw\n",
+    "etac=wid/wac#................#Compressor efficiency\n",
+    "print \"Compressor efficiency = %0.2f %%\"%(etac*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.37 PAGE 778"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 32,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Isentropic efficiency = 74.46 %\n",
+      "Power required to drive the coompressor = 190.69 kW\n",
+      "Overall efficiency = 72.92 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "m=2.5#..........#Air flow rate in kg/s\n",
+    "p1=1#........#Inlet pressure in bar\n",
+    "t1=290#............#Inlet temperature in bar\n",
+    "C1=80#..........#Inlet Velocity in m/s\n",
+    "p2=1.5#........#pressure after compression in bar\n",
+    "t2=345#............#temperature after compression in bar\n",
+    "C2=220#..........#Velocity after compression in m/s\n",
+    "cp=1.005#...........#Specific heat at constant pressure in kJ/kgK\n",
+    "ga=1.4#............#Ratio of specific heats\n",
+    "R=287#..............#Gas constant for air in kJ/kgK\n",
+    "#Calculations\n",
+    "t21=t1*((p2/p1)**((ga-1)/ga))#\n",
+    "wisen=cp*(t21-t1)+((C2*C2)-(C1*C1))/(2*1000)#.....#Isentropic work done in kJ/kg\n",
+    "w=cp*(t2-t1)+((C2*C2)-(C1*C1))/(2*1000)#.....#Actual work done (in impeller) in kJ/kg\n",
+    "etaisen=wisen/w#...............#Isentropic efficiency\n",
+    "print \"Isentropic efficiency = %0.2f %%\"%(etaisen*100)\n",
+    "P=m*w#..........#Power required to drive the coompressor in kW\n",
+    "print \"Power required to drive the coompressor = %0.2f kW\"%P\n",
+    "t3=(((C2*C2)-(C1*C1))/(2*1000*cp))+t2#....#Temperature of air after leaving the diffuser in K\n",
+    "p3=p2*((t3/t2)**(ga/(ga-1)))#..........#Pressure of air after leaving the diffuser in bar\n",
+    "t31=t1*((p3/p1)**((ga-1)/ga))#...........#Delivery temperature from diffuser in K\n",
+    "etao=(t31-t1)/(t3-t1)#...............#Overall efficiency \n",
+    "print \"Overall efficiency = %0.2f %%\"%(etao*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.38 PAGE 779"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 33,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Actual rise in temperature = 165.00\n",
+      "Tip diameter of the impeller = 40.99 cm\n",
+      "Power required = 1459.26 kW\n",
+      "Diameter of the eye = 28.17 cm\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "ma=528#.............#Air flow in kg/min\n",
+    "m=ma/60#.............#Air flow in kg/s\n",
+    "p1=1#........#Inlet pressure in bar\n",
+    "t1=293#............#Inlet temperature in bar\n",
+    "N=20000#..............#Compressor rpm\n",
+    "etaisen=0.8#.........#Isentropic efficiency\n",
+    "po1=1#.........#Static pressure in bar\n",
+    "p02=4#...........#Final total pressure in bar\n",
+    "C1=145#.........#Velocity of air when entering the impeller in m/s\n",
+    "rwt=0.9#..........#Ratio of whirl speed to tip speed \n",
+    "dh=0.12#........#Hub diameter in m\n",
+    "cp=1.005#...........#Specific heat at constant pressure in kJ/kgK\n",
+    "ga=1.4#............#Ratio of specific heats\n",
+    "R=287#..............#Gas constant for air in kJ/kgK\n",
+    "#Calculations\n",
+    "t01=t1+((C1*C1)/(2*cp*1000))#..........#Stagnation temperature at the inlet to the machine in K\n",
+    "p01=p1*((t01/t1)**(ga/(ga-1)))#.....#Stagnation pressure at the inlet to the machine in bar\n",
+    "t021=t01*((p02/p01)**((ga-1)/ga))#\n",
+    "deltisen=t021-t01#.........#Isentropic rise in temperature in K\n",
+    "delt=round(deltisen/etaisen)#........#Actual rise in temperature \n",
+    "print \"Actual rise in temperature = %0.2f\"%delt\n",
+    "wc=cp*delt#.........#Work consumed by compressor in kJ/kg\n",
+    "Cbl2=sqrt(wc*1000/rwt)#\n",
+    "d2=Cbl2*60/(pi*N)#..........#Tip diameter of the impeller in m\n",
+    "print \"Tip diameter of the impeller = %0.2f cm\"%(d2*100)\n",
+    "P=m*wc#............#Power required in kW\n",
+    "print \"Power required = %0.2f kW\"%P\n",
+    "rho1=(p1*10**5)/(R*t1)#.......#Density at entry in kg/m**3\n",
+    "d1=sqrt(((m*4)/(C1*rho1*pi))+(dh**2))#.......#Eye diameter in m\n",
+    "print \"Diameter of the eye = %0.2f cm\"%(d1*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.39 PAGE 780"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 34,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Final temperature of air = 466.65 Kevin\n",
+      "Theoretical power = 2282.94 kW\n",
+      "Impeller diameter at outlet = 84.10 cm\n",
+      "Impeller diameter at inlet = 42.05 cm\n",
+      "Breadth of impeller at inlet = 14.92 cm\n",
+      "Impeller blade angle at inlet = 15.73 degrees\n",
+      "Diffuser blade angle at inlet = 8.89 degrees\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt,atan\n",
+    "# Initialisation of Variables\n",
+    "N=10000#.................#Compressor rpm\n",
+    "v=660#............#Volume of air delivered in m**3/min\n",
+    "p1=1#.................#Inlet pressure in bar\n",
+    "t1=293#.............#Inlet temperature in K\n",
+    "rp=4#.............#Pressure ratio\n",
+    "etaisen=0.82#........#Isentropic efficiency\n",
+    "Cf2=62#...............#Flow velocity in m/s\n",
+    "rr=2#.............#Ratio of outer radius of impeller to inner radius of impeller\n",
+    "ka=0.9#..............#Blade area co efficient\n",
+    "fis=0.9#...........#Slip factor\n",
+    "cp=1.005#..............#Specific heat at constant pressure in kJ/kgK\n",
+    "ga=1.4#............#Ratio of specific heats\n",
+    "R=287#..............#Gas constant for air in kJ/kgK\n",
+    "#Calculations\n",
+    "t21=t1*(rp**((ga-1)/ga))#\n",
+    "Cf1=Cf2#\n",
+    "t2=t1+((t21-t1)/etaisen)#..........#Final temperature of air\n",
+    "m=(p1*10**5*v/60)/(R*t1)#...............#Mass flow rate in m**3/s\n",
+    "P=m*cp*(t2-t1)#.........#Theoretical power in kW\n",
+    "print \"Final temperature of air = %0.2f Kevin\"%t2\n",
+    "print \"Theoretical power = %0.2f kW\"%P\n",
+    "Cbl2=sqrt(1000*cp*(t2-t1)/fis)#\n",
+    "d2=60*Cbl2/(pi*N)#..........#Impeller diameter at outlet in m\n",
+    "d1=d2/rr#...............#Impeller diameter at inlet in m\n",
+    "print \"Impeller diameter at outlet = %0.2f cm\"%(d2*100)\n",
+    "print \"Impeller diameter at inlet = %0.2f cm\"%(d1*100)\n",
+    "b1=(v/60)/(2*pi*(d1/2)*Cf1*ka)#.........#Breadth of impeller at inlet in m\n",
+    "print \"Breadth of impeller at inlet = %0.2f cm\"%(b1*100)\n",
+    "Cbl1=Cbl2/rr#\n",
+    "beta1=(atan(Cf1/Cbl1))*180/pi#\n",
+    "al2=(atan(Cf2/(fis*Cbl2)))*180/pi#\n",
+    "print \"Impeller blade angle at inlet = %0.2f degrees\"%(beta1)\n",
+    "print \"Diffuser blade angle at inlet = %0.2f degrees\"%(al2,)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.40 PAGE 780"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 35,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "\n",
+      "Blade angles  \n",
+      "\n",
+      "\t Blade angle at the inlet of the impeller: beta 1=25.869916 \n",
+      "\t Blade angle at the outlet of the impeller: beta 2=34.206408 \n",
+      "\t Absolute angle at the tip of impeller: alpha 2=21.610499\n",
+      "\n",
+      "\n",
+      "Breadth of the blade at inlet = 7.35 cm\n",
+      "Breadth of the blade at outlet = 2.89 cm\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt,atan\n",
+    "# Initialisation of Variables\n",
+    "v1=4.8#......#Volume of air compressed in m**3/s\n",
+    "p1=1#....#Inlet pressure in bar\n",
+    "t1=293#........#Inlet pressure in K\n",
+    "n=1.5#........#Compression index\n",
+    "Cf1=65#......#Air flow velocity at inlet in m/s\n",
+    "Cf2=Cf1#......#Flow velocity is same at inlet and outlet\n",
+    "d1=0.32#..........#Inlet impeller diameter in m\n",
+    "d2=0.62#........#Outlet impeller diameter in m\n",
+    "N=8000#........#Blower rpm\n",
+    "cp=1.005#......#Specific heat at constant pressure in kJ/kgK\n",
+    "#Calculations\n",
+    "t21=t1*((n/p1)**((n-1)/n))#....#Temperature at the outlet of compressor in K\n",
+    "Cbl1=(pi*d1*N)/60#......#Peripheral velocity at inlet in m/s\n",
+    "Cbl2=(pi*N*d2)/60#......#Tip peripheral velocity at outlet in m/s\n",
+    "Cw2=(cp*(t21-t1)*1000)/Cbl2#\n",
+    "be1=(atan(Cf1/Cbl1))*180/pi#\n",
+    "be2=(atan(Cf2/(Cbl2-Cw2)))*180/pi#......#Blade angles at the tip of the impeller\n",
+    "al2= (atan(Cf2/Cw2))*180/pi# \n",
+    "print \"\\nBlade angles  \\n\\n\\t Blade angle at the inlet of the impeller: beta 1=%f \\n\\t Blade angle at the outlet of the impeller: beta 2=%f \\n\\t Absolute angle at the tip of impeller: alpha 2=%f\\n\\n\"%(be1,be2,al2)\n",
+    "b1=v1/(2*pi*(d1/2)*Cf1)#........#Breadth of blade at inlet in m\n",
+    "print \"Breadth of the blade at inlet = %0.2f cm\"%(b1*100)\n",
+    "v2=(v1*t21*p1)/(n*t1)#..............#Discharge at the outlet in m**3/s\n",
+    "b2=v2/(2*pi*(d2/2)*Cf2)#........#Breadth of blade at outlet in m\n",
+    "print \"Breadth of the blade at outlet = %0.2f cm\"%(b2*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.41 PAGE 781"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 36,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Diameter of the impeller = 0.56 m\n",
+      "Power input to compressor = 2951.61 kW\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "m=16.5#.......#Air flow in kg/s\n",
+    "rp=4#........#Pressure ratio\n",
+    "N=15000#.........#Compressor rpm\n",
+    "t01=293#.........#Inlet head temperature\n",
+    "fis=0.9#...........#Slip factor\n",
+    "fiw=1.04#.........#Power input factor\n",
+    "etaisen=0.8#.......#Isentropic efficiency\n",
+    "cp=1.005#........#Specific heat at constant pressure in kJ/kgK\n",
+    "ga=1.4#......#Ratio of specific heats\n",
+    "#Calculations\n",
+    "t021=t01*(rp**((ga-1)/ga))#\n",
+    "delt=(t021-t01)/etaisen#\n",
+    "Cbl2=sqrt((1000*cp*delt)/(fiw*fis))#\n",
+    "D=(60*Cbl2)/(pi*N)#..............#Diameter of impeller\n",
+    "print \"Diameter of the impeller = %0.2f m\"%D\n",
+    "P=m*cp*delt#\n",
+    "print \"Power input to compressor = %0.2f kW\"%P"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.42 PAGE 781"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 37,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Total head temperature = 447.09 K\n",
+      "Static temperature at outlet = 439.93 K\n",
+      "Static pressure at exit = 3.45 bar\n",
+      "Static temperature at inlet = 278.25 K\n",
+      "Static pressure at inlet = 0.90 bar\n",
+      "Static pressure ratio : 3.8237\n",
+      "Work done on air = 159.89 kJ/kg\n",
+      "Power required to drive the compressor = 1918.67 kW\n"
+     ]
+    }
+   ],
+   "source": [
+    "\n",
+    "# Initialisation of Variables\n",
+    "rp=3.6#..........#Pressure ratio\n",
+    "die=0.35#.......#Diameter of inlet eye of compressor in m\n",
+    "Cf=140#..........#Axial velocity in m/s\n",
+    "m=12#.............#Mass flow in kg/s\n",
+    "Cbl2=120#.........#Velocity in the delivery duct in m/s\n",
+    "Ci=460#..........#The tip speed of the impeller in m/s\n",
+    "N=16000#............#Speed of impeller in rpm\n",
+    "etaisen=0.8#.......#Isentropic efficiency\n",
+    "pc=0.73#........#Pressure co efficient\n",
+    "pa=1.013#..........#Ambient pressure in bar\n",
+    "ta=273+15#................#Ambient temperature in K\n",
+    "ga=1.4#..........#Ratio of specific heats\n",
+    "cp=1.005#.........#Specific heat at constant pressure in kJ/kgK\n",
+    "R=0.287#........#Gas constant in kJ/kgK\n",
+    "#Calculations\n",
+    "delt=((ta*((rp**((ga-1)/ga))-1))/etaisen)#.......#Rise in temperature\n",
+    "t02=ta+delt#............#Total head temperature in K\n",
+    "print \"Total head temperature = %0.2f K\"%t02\n",
+    "t2=t02-((Cbl2*Cbl2)/(2*cp*1000))#..........#Static temperature at outlet in K\n",
+    "print \"Static temperature at outlet = %0.2f K\"%t2\n",
+    "p02=pa*rp#\n",
+    "p2=p02/(1+((Cbl2*Cbl2)/(2*R*t2*1000)))#...........#Static pressure at exit in bar\n",
+    "print \"Static pressure at exit = %0.2f bar\"%p2\n",
+    "t1=ta-((Cf*Cf)/(2*cp*1000))#.............#Static temperature at inlet in K\n",
+    "print \"Static temperature at inlet = %0.2f K\"%t1\n",
+    "p1=pa/(1+((Cf*Cf)/(2*R*t1*1000)))#...........#Static pressure at inlet in bar\n",
+    "print \"Static pressure at inlet = %0.2f bar\"%p1\n",
+    "rp=p2/p1#.....#Static pressure ratio\n",
+    "print \"Static pressure ratio : %0.4f\"%rp\n",
+    "W=cp*delt#...........#Work done on air in kJ/kg of air\n",
+    "print \"Work done on air = %0.2f kJ/kg\"%W\n",
+    "P=m*cp*delt#..........#Power required to drive the compressor in kW\n",
+    "print \"Power required to drive the compressor = %0.2f kW\"%P"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.43 PAGE 782"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 38,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Temperature rise of air while passing through compressor: 159.09 \n",
+      "Pressure ratio : 3.8237\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt\n",
+    "# Initialisation of Variables\n",
+    "t1=300#.........#Inlet temperature in K\n",
+    "N=18000#.............#Compressor rpm\n",
+    "etaisen=0.76#.......#Isentropic efficiency\n",
+    "od=0.55#......#Outer diameter of blade tip\n",
+    "sf=0.82#......#Slip factor\n",
+    "cp=1.005#.........#Specific heat capacity at constant pressure in kJ/kgK\n",
+    "ga=1.4#.............#Ratio of specific heats\n",
+    "#Calculations\n",
+    "Cbl2=(pi*od*N)/60#W=Cbl2*Cbl2*sf/1000#...........#Work done per kg of air in kW\n",
+    "delt=W/cp#..............#Temperature rise of air while passing through compressor \n",
+    "print \"Temperature rise of air while passing through compressor: %0.2f \"%delt\n",
+    "t21=(etaisen*delt)+t1#rp=((t21/t1)**(ga/(ga-1)))#.....#Pressure ratio\n",
+    "print \"Pressure ratio : %0.4f\"%rp"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.44 PAGE 782"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 39,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Pressure rise = 0.15 bar\n",
+      "Work done per kg of air = 27.54 kW\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt,tan\n",
+    "# Initialisation of Variables\n",
+    "Cbl=240#........#Mean blade velocity in m/s\n",
+    "Cf=190#.........#Air flow velocity in m/s\n",
+    "al1=45#al2=14#.........#Blade angels in degrees\n",
+    "rho=1#.........#Density of air in kg/m**3\n",
+    "#Calculations \n",
+    "pr=(1/2)*(rho*Cf*Cf/(10**5))*(((tan(al1*pi/180))**2)-((tan(al2*pi/180))**2))#.......#Pressure rise in bar\n",
+    "print \"Pressure rise = %0.2f bar\"%pr\n",
+    "W=Cbl*Cf/1000*((tan(al1*pi/180))-(tan(al2*pi/180)))#.............#Work done per kg of air in kW\n",
+    "print \"Work done per kg of air = %0.2f kW\"%W"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.45 PAGE 783"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 40,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Work done by the machine = 174.52 kJ/kg\n",
+      "\n",
+      "Blade angels are as follows (In degrees)\n",
+      "\n",
+      "alpha1=18.091622\tbeta1=59.136727\n",
+      "\n",
+      "alpha2=59.136727\tbeta2=18.091622\n",
+      "\n",
+      "\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt,atan\n",
+    "# Initialisation of Variables\n",
+    "etaisen=0.82#.......#Overall isentropic efficiency \n",
+    "N=8#............#No of stages\n",
+    "t1=293#...........#Inlet temperature in K\n",
+    "ga=1.4#............#Ratio of specific heats\n",
+    "rp=4#.............#Pressure ratio\n",
+    "Rd=0.5#................#Reaction factor\n",
+    "Cbl=180#.................#Mean blade speed in m/s\n",
+    "Cf=90#...............#Air flow velocity in m/s\n",
+    "cp=1.005#.........#Specific heat at constant pressure in kJ/kgK\n",
+    "#Calculations\n",
+    "t21=t1*(rp**((ga-1)/ga))#\n",
+    "t2=((t21-t1)/etaisen)+t1#\n",
+    "wrt=cp*(t2-t1)#.........#Work done by the machine in kJ/kg\n",
+    "print \"Work done by the machine = %0.2f kJ/kg\"%wrt\n",
+    "be1=atan(((cp*(t2-t1)*1000/(Cf*Cbl*N))+(Cbl/Cf))/2)*180/pi#\n",
+    "al1=atan((Cbl/Cf)-tan(be1*pi/180))*180/pi#\n",
+    "print \"\\nBlade angels are as follows (In degrees)\\n\\nalpha1=%f\\tbeta1=%f\\n\\nalpha2=%f\\tbeta2=%f\\n\\n\"%(al1,be1,be1,al1)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.46 PAGE 784"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 41,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Flow velocity = 95.45 m/s\n",
+      "No of stages :  8.0\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt,tan\n",
+    "# Initialisation of Variables\n",
+    "etaisen=0.85#.......#Overall isentropic efficiency\n",
+    "t1=293#...........#Inlet temperature in K\n",
+    "rp=4#.............#Pressure ratio\n",
+    "Rd=0.5#................#Reaction factor\n",
+    "Cbl=180#.................#Mean blade speed in m/s\n",
+    "wip=0.82#..............#Work input factor\n",
+    "al1=12#be1=42#......#Blade angels in degrees\n",
+    "ga=1.4#............#Ratio of specific heats  \n",
+    "cp=1.005#.........#Specific heat at constant pressure in kJ/kgK\n",
+    "#Calculations\n",
+    "t21=t1*(rp**((ga-1)/ga))#\n",
+    "t2=((t21-t1)/etaisen)+t1#\n",
+    "wrt=cp*(t2-t1)#.........#Theoretical work required in kJ/kg\n",
+    "Cf=Cbl/(tan(al1*pi/180)+tan(be1*pi/180))#\n",
+    "Cw1=Cf*tan(al1*pi/180)#Cw2=Cf*tan(be1*pi/180)#\n",
+    "wcps=Cbl*(Cw2-Cw1)*wip/1000#.............#Work consumed per stage in kJ/kg\n",
+    "N=round(wrt/wcps)#.......#No of stages\n",
+    "print \"Flow velocity = %0.2f m/s\"%Cf\n",
+    "print \"No of stages : \",N"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.47 PAGE 784"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 42,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "\n",
+      "Blade angels are as follows (In degrees)\n",
+      "\n",
+      "alpha1=4.924070\t\tbeta1=59.410637\n",
+      "\n",
+      "alpha2=59.410637\tbeta2=4.924070\n",
+      "\n",
+      "\n",
+      "Power required by the compressor = 184.95 kW\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt,atan,tan\n",
+    "# Initialisation of Variables\n",
+    "rp=5#..........#Stagnation pressure ratio ga\n",
+    "etaisen=0.92#.......#Overall isentropic efficiency\n",
+    "t1=290#.............#Inlet stagnation temperature in K\n",
+    "p1=1#...............#Inlet stagnation pressure in bar\n",
+    "Cbl=160#...........#Mean blade speed in m/s\n",
+    "ga=1.4#...........#Ratio of specific heats\n",
+    "Rd=0.5#............#Degree of reaction\n",
+    "Cf=90#................#Axial velocity of air through compressor in m/s\n",
+    "N=8#.............#No of stages\n",
+    "m=1#.........#Mass flow in kg/s\n",
+    "cp=1.005#............#Specific heat at constant pressure in kJ/kgK\n",
+    "#Calculations\n",
+    "tN1=t1*(rp**((ga-1)/ga))#......#Temperature at the end of compression stage due to isentropic expansion in K\n",
+    "tN=((tN1-t1)/etaisen)+t1#\n",
+    "be1=atan(((cp*(tN-t1)*1000/(Cf*Cbl*N))+(Cbl/Cf))/2)*180/pi#\n",
+    "al1=atan((Cbl/Cf)-tan(be1*pi/180))*180/pi#\n",
+    "print \"\\nBlade angels are as follows (In degrees)\\n\\nalpha1=%f\\t\\tbeta1=%f\\n\\nalpha2=%f\\tbeta2=%f\\n\\n\"%(al1,be1,be1,al1)\n",
+    "P=m*cp*(tN-t1)#..........#Power required by the compressor in kW\n",
+    "print \"Power required by the compressor = %0.2f kW\"%P"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.48 PAGE 785"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 44,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Stagnation polytropic efficiency = 87.59 %\n",
+      "No of stages :  27.0\n",
+      "Inlet temperature = 295.35 K\n",
+      "Inlet pressure = 0.95 bar\n",
+      "Height of the blade in the first stage = 28.23 cm\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt,cos,log,tan,atan\n",
+    "# Initialisation of Variables\n",
+    "rp=4#........#Stagnation pressure ratio\n",
+    "etaisen=0.85#.....#Stagnation isentropic efficiency\n",
+    "p1=1#.............#Inlet stagnation pressure in bar\n",
+    "t1=300#...........#Inlet stagnation temperature in K\n",
+    "Rd=0.5#............#Degree of reaction\n",
+    "Cu=180#...........#Mean blade speed in m/s\n",
+    "Wd=0.9#...........#Work done factor\n",
+    "htr=0.42#.......#Hub tip ratio\n",
+    "al1=12#be2=al1#.......#Relative air angle at rotor inlet in degrees\n",
+    "al2=32#be1=al2#........#Relative air angle at rotor at outlet in degrees\n",
+    "ga=1.4#...........#Ratio of specific heats\n",
+    "cp=1.005#..........#Specific heat capacity at constant pressure in kJ/kgK\n",
+    "R=287#..........#Gas constant in J/kgK\n",
+    "m=19.5#..........#Mass flow in kg/s\n",
+    "#Calculations\n",
+    "tN1=t1*(rp**((ga-1)/ga))#......#Temperature at the end of compression stage due to isentropic expansion in K\n",
+    "tN=((tN1-t1)/etaisen)+t1#\n",
+    "etap=log(rp**((ga-1)/ga))/log(tN/t1)#...........#Stagnation polytropic efficiency\n",
+    "print \"Stagnation polytropic efficiency = %0.2f %%\"%(etap*100)\n",
+    "Cf=Cu/(tan(al1*pi/180)+tan(be1*pi/180))#\n",
+    "Cw1=Cf*tan(al1*pi/180)\n",
+    "Cw2=Cf*tan(al2*pi/180)#\n",
+    "wcps=Cu*(Cw2-Cw1)*Wd/1000#.............#Work consumed per stage in kJ/kg\n",
+    "wc=cp*(tN-t1)#...............#Work consumed by compressor in kJ/kg\n",
+    "N=round(wc/wcps)#.......#No of stages\n",
+    "print \"No of stages : \",N\n",
+    "C1=Cf/cos(al1*pi/180)#.......#Absolute velocity at exit from guide vanes in m/s\n",
+    "ti=t1-((C1*C1)/(2*cp*1000))#..........#Inlet temperature in K\n",
+    "print \"Inlet temperature = %0.2f K\"%ti\n",
+    "pi=p1*((ti/t1)**(ga/(ga-1)))#......#Inlet pressure in bar\n",
+    "print \"Inlet pressure = %0.2f bar\"%pi\n",
+    "rho1=(pi*10**5)/(R*ti)#.............#Density of air approaching the first stage\n",
+    "r1=sqrt(m/(rho1*pi*Cf*(1-(htr**2))))#\n",
+    "rh=r1*htr#\n",
+    "l=r1-rh#............#Height of the blade in the first stage in m\n",
+    "print \"Height of the blade in the first stage = %0.2f cm\"%(l*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 20.49 PAGE 785"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 1,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Delivery pressure = 5.57 bar\n",
+      "No of stages :  11.0\n",
+      "Overall efficiency = 84.86 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi, sqrt,cos,log,tan,atan,exp\n",
+    "# Initialisation of Variables\n",
+    "ma=20#..........#Air flow rate in kg/s\n",
+    "p1=1#.........#Inlet stagnation pressure in bar\n",
+    "t1=290#.........#Inlet stagnation temperature in Kelvin\n",
+    "t2=305#.........#Temperature at the end of first stage in K\n",
+    "etapc=0.88#.....#Polytropic efficiency of compression\n",
+    "P=4350#......#Power consumed by compressor in kW\n",
+    "ga=1.4#.....#Ratio of specific heats\n",
+    "cp=1.005#......#Specific heat at constant pressure \n",
+    "#Calculations\n",
+    "p2byp1=(exp(etapc*log(t2/t1)))**(ga/(ga-1))#\n",
+    "tN=(P/(ma*cp))+t1#\n",
+    "pN=p1*((tN/t1)**((etapc*ga)/(ga-1)))#......#Delivery pressure in bar\n",
+    "print \"Delivery pressure = %0.2f bar\"%pN\n",
+    "N=log(pN/p1)/log(p2byp1)#...........#No of stages \n",
+    "print \"No of stages : \",round(N)\n",
+    "tN1=t1*((pN/p1)**((ga-1)/ga))#\n",
+    "etao=(tN1-t1)/(tN-t1)#...............#Overall efficiency\n",
+    "print \"Overall efficiency = %0.2f %%\"%(etao*100)"
+   ]
+  }
+ ],
+ "metadata": {
+  "kernelspec": {
+   "display_name": "Python 2",
+   "language": "python",
+   "name": "python2"
+  },
+  "language_info": {
+   "codemirror_mode": {
+    "name": "ipython",
+    "version": 2
+   },
+   "file_extension": ".py",
+   "mimetype": "text/x-python",
+   "name": "python",
+   "nbconvert_exporter": "python",
+   "pygments_lexer": "ipython2",
+   "version": "2.7.9"
+  }
+ },
+ "nbformat": 4,
+ "nbformat_minor": 0
+}
diff --git a/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER21_2.ipynb b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER21_2.ipynb
new file mode 100644
index 00000000..185ffd2e
--- /dev/null
+++ b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER21_2.ipynb
@@ -0,0 +1,1255 @@
+{
+ "cells": [
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "# CHAPTER 21 - Gas turbines and jet propulsion"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 21.1 PAGE 848"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 3,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Power developed = 250.22 kW/kg of air\n",
+      "Thermal efficiency = 17.96 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "p1=1#.........#Pressure of air while entering the turbine in bar\n",
+    "t1=293#........#Temperature of air entering the turbine in K\n",
+    "p2=4#.........#Pressure of air after compression in bar\n",
+    "etac=0.8#....#Efficiency of compressor\n",
+    "etat=0.85#.....#Efficiency of turbine\n",
+    "afr=90#........#Air fuel ratio\n",
+    "ma=3#...........#Mass of air in kg/s\n",
+    "ga=1.4#........#Ratio of specific heats\n",
+    "cp=1#.............#Specific heat at constant pressure in kJ/kgK\n",
+    "C=41800#.............#Calorific value of fuel in kJ/kg\n",
+    "#Calculations\n",
+    "t2=t1*((p2/p1)**((ga-1)/ga))#...............#Ideal temperature of air after compression in K\n",
+    "t21=((t2-t1)/etac)+t1#..............#Actual temperature of air after compression in K\n",
+    "t3=round((C/((afr+1)*cp))+t21)#..............#Temperature before expansion in turbine in K\n",
+    "p4=p1#\n",
+    "p3=p2#\n",
+    "t4=t3*((p4/p3)**((ga-1)/ga))#............#Ideal temperature after expansion in turbine in K\n",
+    "t41=t3-(etat*(t3-t4))#.................#Actual temperature after expansion in turbine in K\n",
+    "wt=((afr+1)/afr)*cp*(t3-t41)#........#Work done by turbine  in kJ/kg of air\n",
+    "wc=round(1*cp*(t21-t1))#.................#Work done by compression in kJ/kg of air\n",
+    "wnet=wt-wc#..........#Net work done in kJ/kg\n",
+    "P=wnet*ma#.................#Power developed in kW/kg of air\n",
+    "print \"Power developed = %0.2f kW/kg of air\"%P\n",
+    "qs=(1/afr)*C#................#Heat supplied in kJ/kg of air\n",
+    "etath=wnet/qs#................#Thermal efficiency\n",
+    "print \"Thermal efficiency = %0.2f %%\"%(etath*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 21.2 PAGE 848"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 1,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Power developed = 770.31 kW/kg of air\n"
+     ]
+    }
+   ],
+   "source": [
+    "# Initialisation of Variables\n",
+    "t1=288#........#Temperature of air entering the turbine in K\n",
+    "t3=883#..............#Temperature before expansion in turbine in K\n",
+    "etac=0.8#....#Efficiency of compressor\n",
+    "etat=0.82#.....#Efficiency of turbine\n",
+    "rp=6#...........#Pressure ratio\n",
+    "ma=16#...........#Mass of air in kg/s\n",
+    "gac=1.4#........#Ratio of specific heats for compression process\n",
+    "gae=1.333#............#Ratio of specific heats for expansion process\n",
+    "cpc=1.005#.............#Specific heat at constant pressure in kJ/kgK during compression process\n",
+    "cpe=1.11#.............#Specific heat at constant pressure in kJ/kgK during expansion process\n",
+    "C=41800#.............#Calorific value of fuel in kJ/kg\n",
+    "#Calculations\n",
+    "t2=t1*((rp)**((gac-1)/gac))#...............#Ideal temperature of air after compression in K\n",
+    "t21=((t2-t1)/etac)+t1#..............#Actual temperature of air after compression in K\n",
+    "t4=t3/((rp)**((gae-1)/gae))#............#Ideal temperature after expansion in turbine in K\n",
+    "t41=t3-(etat*(t3-t4))#.................#Actual temperature after expansion in turbine in K\n",
+    "wt=cpe*(t3-t41)#........#Work done by turbine  in kJ/kg of air\n",
+    "wc=(1*cpc*(t21-t1))#.................#Work done by compression in kJ/kg of air\n",
+    "wnet=wt-wc#..........#Net work done in kJ/kg\n",
+    "P=wnet*ma#.................#Power developed in kW/kg of air\n",
+    "print \"Power developed = %0.2f kW/kg of air\"%P"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 21.3 PAGE 849"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 2,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Thermal efficiency = 32.65 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "# Initialisation of Variables\n",
+    "p1=1#.........#Pressure of air while entering the turbine in bar\n",
+    "t1=300#........#Temperature of air entering the turbine in K\n",
+    "p2=6.2#.........#Pressure of air after compression in bar\n",
+    "etac=0.88#....#Efficiency of compressor\n",
+    "etat=0.9#.....#Efficiency of turbine\n",
+    "far=0.017#........#Fuel air ratio\n",
+    "ga=1.4#........#Ratio of specific heats for compression\n",
+    "gae=1.333#........#Ratio of specific heats for expansion\n",
+    "cp=1.147#.............#Specific heat at constant pressure in kJ/kgK during expansion\n",
+    "cpc=1.005#.............#Specific heat at constant pressure in kJ/kgK during compression\n",
+    "C=44186#.............#Calorific value of fuel in kJ/kg\n",
+    "#Calculations\n",
+    "t2=t1*((p2/p1)**((ga-1)/ga))#...............#Ideal temperature of air after compression in K\n",
+    "t21=((t2-t1)/etac)+t1#..............#Actual temperature of air after compression in K\n",
+    "t3=(((C*far)/((far+1)*cpc))+t21)#..............#Temperature before expansion in turbine in K\n",
+    "p4=p1#\n",
+    "p3=p2#\n",
+    "t4=t3*((p4/p3)**((gae-1)/gae))#............#Ideal temperature after expansion in turbine in K\n",
+    "t41=t3-(etat*(t3-t4))#.................#Actual temperature after expansion in turbine in K\n",
+    "wt=(cp*(t3-t41))#........#Work done by turbine  in kJ/kg of air\n",
+    "wc=round(1*cpc*(t21-t1))#.................#Work done by compression in kJ/kg of air\n",
+    "wnet=wt-wc#..........#Net work done in kJ/kg\n",
+    "qs=(far)*C#................#Heat supplied in kJ/kg of air\n",
+    "etath=wnet/qs#................#Thermal efficiency\n",
+    "print \"Thermal efficiency = %0.2f %%\"%(etath*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 21.4 PAGE 850"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 3,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Air fuel ratio is 56:1\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "t1=300#........#Temperature of air entering the turbine in K\n",
+    "t3=1148#..............#Temperature before expansion in turbine in K\n",
+    "etac=0.8#....#Efficiency of compressor\n",
+    "etat=0.852#.....#Efficiency of turbine\n",
+    "rp=4#...........#Pressure ratio\n",
+    "p1=1#...............#Pressure of air before entering compressor\n",
+    "ga=1.4#........#Ratio of specific heats\n",
+    "cp=1.0#.............#Specific heat at constant pressure in kJ/kgK \n",
+    "C=42000#.............#Calorific value of fuel in kJ/kg\n",
+    "perlcc=10#............#Percent loss of calorific value of fuel in combustion chamber\n",
+    "#Calculations\n",
+    "p2=p1*rp#.................#Pressure of air after compression in  bar\n",
+    "etacc=(100-perlcc)/100#.......#Efficiency of combustion chamber\n",
+    "t2=t1*((rp)**((ga-1)/ga))#...............#Ideal temperature of air after compression in K\n",
+    "t21=((t2-t1)/etac)+t1#..............#Actual temperature of air after compression in K\n",
+    "afr=((C*etacc)/(cp*(t3-t21)))-1#........#Air fuel ratio\n",
+    "print \"Air fuel ratio is %d:1\"%round(afr)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 21.5 PAGE 851"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 3,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Thermal efficiency = 15.92 %\n",
+      "The work ratio is 0.259290\n"
+     ]
+    }
+   ],
+   "source": [
+    "# Initialisation of Variables\n",
+    "t1=300#........#Temperature of air entering the turbine in K\n",
+    "t3=883#..............#Temperature before expansion in turbine in K\n",
+    "etac=0.8#....#Efficiency of compressor\n",
+    "etat=0.852#.....#Efficiency of turbine\n",
+    "rp=4#...........#Pressure ratio\n",
+    "p1=1#...............#Pressure of air before entering compressor\n",
+    "ga=1.4#........#Ratio of specific heats\n",
+    "cp=1.11#.............#Specific heat at constant pressure in kJ/kgK \n",
+    "C=42000#.............#Calorific value of fuel in kJ/kg\n",
+    "perlcc=10#............#Percent loss of calorific value of fuel in combustion chamber\n",
+    "#Calculations\n",
+    "p2=p1*rp#.................#Pressure of air after compression in  bar\n",
+    "etacc=(100-perlcc)/100#.......#Efficiency of combustion chamber\n",
+    "t2=t1*((rp)**((ga-1)/ga))#...............#Ideal temperature of air after compression in K\n",
+    "t21=((t2-t1)/etac)+t1#..............#Actual temperature of air after compression in K\n",
+    "qs=cp*(t3-t21)#...................#Heat supplied in kJ/kg\n",
+    "t4=t3/((rp)**((ga-1)/ga))#............#Ideal temperature after expansion in turbine in K\n",
+    "t41=t3-(etat*(t3-t4))#.................#Actual temperature after expansion in turbine in K\n",
+    "wt=cp*(t3-t41)#........#Work done by turbine  in kJ/kg of air\n",
+    "wc=(1*cp*(t21-t1))#.................#Work done by compression in kJ/kg of air\n",
+    "wnet=wt-wc#..........#Net work done in kJ/kg\n",
+    "etath=wnet/qs#................#Thermal efficiency\n",
+    "print \"Thermal efficiency = %0.2f %%\"%(etath*100)\n",
+    "wrr=wnet/wt#...................#Work ratio\n",
+    "print \"The work ratio is %f\"%wrr"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 21.6 PAGE 851"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 4,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Quantity of air in circulation = 13.49 kg\n",
+      "Actual heat supplied per kg of air circulation = 552.66 kJ\n",
+      "Thermal efficiency = 14.28 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "# Initialisation of Variables\n",
+    "p1=1#.........#Pressure of air while entering the turbine in bar\n",
+    "t1=293#........#Temperature of air entering the turbine in K\n",
+    "p2=5#.........#Pressure of air after compression in bar\n",
+    "plcc=0.1#.....#Pressure loss in combustion chamber in bar\n",
+    "t3=953#............#Temperature before expansion in turbine in K\n",
+    "etac=0.85#....#Efficiency of compressor\n",
+    "etat=0.8#.....#Efficiency of turbine\n",
+    "etacc=0.85#......#Efficiency of combustion chamber\n",
+    "ga=1.4#........#Ratio of specific heats\n",
+    "cp=1.024#.............#Specific heat at constant pressure in kJ/kgK \n",
+    "P=1065#.............#Power developed by the plant in kW\n",
+    "\n",
+    "#Calculations\n",
+    "p3=p2-plcc#........................#Pressure before expansion in turbine in bar\n",
+    "p4=p1#\n",
+    "t2=t1*((p2/p1)**((ga-1)/ga))#...............#Ideal temperature of air after compression in K\n",
+    "t21=((t2-t1)/etac)+t1#..............#Actual temperature of air after compression in K\n",
+    "t4=t3*((p4/p3)**((ga-1)/ga))#............#Ideal temperature after expansion in turbine in K\n",
+    "t41=t3-(etat*(t3-t4))#.................#Actual temperature after expansion in turbine in K\n",
+    "wt=(cp*(t3-t41))#........#Work done by turbine  in kJ/kg of air\n",
+    "wc=round(1*cp*(t21-t1))#.................#Work done by compression in kJ/kg of air\n",
+    "wnet=wt-wc#..........#Net work done in kJ/kg\n",
+    "ma=P/wnet#.............#Quantity of air in circulation in kg\n",
+    "print \"Quantity of air in circulation = %0.2f kg\"%(ma)\n",
+    "qs=cp*(t3-t21)/etac#..................#Actual heat supplied per kg of air circulation in kJ\n",
+    "print \"Actual heat supplied per kg of air circulation = %0.2f kJ\"%qs\n",
+    "etath=wnet/qs#.............#Thermal efficiency\n",
+    "print \"Thermal efficiency = %0.2f %%\"%(etath*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 21.7 PAGE 852"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 5,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Pressure ratio of low pressure turbine : 2.3042\n",
+      "Temperature of the exhaust from the unit = 672.95 K\n"
+     ]
+    }
+   ],
+   "source": [
+    "# Initialisation of Variables\n",
+    "ma=20#..............#Air flow rate in kg/s\n",
+    "t1=300#........#Temperature of air entering the turbine in K\n",
+    "t3=1000#............#Temperature before expansion in turbine in K\n",
+    "rp=4#...............#Pressure ratio\n",
+    "cp=1#.............#Specific heat at constant pressure in kJ/kgK \n",
+    "ga=1.4#........#Ratio of specific heats\n",
+    "#Calculations\n",
+    "t2=t1*((rp)**((ga-1)/ga))#...............#Temperature of air after compression in K\n",
+    "t4=t3-t2+t1#............#Temperature after expansion in turbine in K\n",
+    "prlp=rp/((t3/t4)**(ga/(ga-1)))#.............#Pressure ratio of low pressure turbine\n",
+    "print \"Pressure ratio of low pressure turbine : %0.4f\"%prlp\n",
+    "t5=t4/((prlp)**((ga-1)/ga))#............#Temperature of the exhaust from the unit in K\n",
+    "print \"Temperature of the exhaust from the unit = %0.2f K\"%t5"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 21.8 PAGE 853"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 6,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Cycle efficiency = 31.04 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "# Initialisation of Variables\n",
+    "p1=1#.........#Pressure of air while entering the turbine in bar\n",
+    "t1=300#........#Temperature of air entering the turbine in K\n",
+    "t21=490#........#Actual temperature of air after compression in K\n",
+    "t3=1000#............#Temperature before expansion in turbine in K\n",
+    "rp=5#.............#Pressure ratio\n",
+    "etac=0.8#....#Efficiency of compressor\n",
+    "etat=0.8#.....#Efficiency of turbine\n",
+    "ga=1.4#........#Ratio of specific heats\n",
+    "cp=1.005#.............#Specific heat at constant pressure in kJ/kgK \n",
+    "#Calculations\n",
+    "t4=t3/((rp)**((ga-1)/ga))#............#Ideal temperature after expansion in turbine in K\n",
+    "t41=t3-(etat*(t3-t4))#.................#Actual temperature after expansion in turbine in K\n",
+    "t5=((t41-t21)*etac)+t21#...........#Temperature of the exhaust from the unit in K\n",
+    "wc=cp*(t21-t1)#.............#Work consumed by compressor in kJ/kg\n",
+    "wt=cp*(t3-t41)#........#Work done by turbine in kJ/kg\n",
+    "qs=cp*(t3-t5)#..........#Heat supplied in kJ/kg\n",
+    "etac=(wt-wc)/qs#.........#Cycle efficiency\n",
+    "print \"Cycle efficiency = %0.2f %%\"%(etac*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 21.9 PAGE 853"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 7,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Thermal efficiency of power turbine = 9.46 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "# Initialisation of Variables\n",
+    "p1=1#.........#Pressure of air while entering the turbine in bar\n",
+    "t1=288#........#Temperature of air entering the turbine in K\n",
+    "p2=8#.........#Pressure of air after compression in bar\n",
+    "t3=1173#.............#Temperature before expansion in turbine in K\n",
+    "etac=0.76#....#Efficiency of compressor\n",
+    "etat=0.86#.....#Efficiency of turbine\n",
+    "ma=23#.........#Quantity of air circulation in kg/s\n",
+    "ga=1.4#........#Ratio of specific heats for compression\n",
+    "gag=1.34#........#Ratio of specific heats for expansion\n",
+    "cp=1.005#.............#Specific heat at constant pressure in kJ/kgK \n",
+    "cpg=1.128#.............#Specific heat at constant pressure in kJ/kgK\n",
+    "C=4200#.............#Calorific value of fuel in kJ/kg\n",
+    "etamech=0.95#........#Mechanical efficiency\n",
+    "etagen=0.96#.........#Generator efficiency\n",
+    "#Calculations\n",
+    "t2=t1*((p2/p1)**((ga-1)/ga))#...............#Ideal temperature of air after compression in K\n",
+    "t21=((t2-t1)/etac)+t1#..............#Actual temperature of air after compression in K\n",
+    "p4=p1#p3=p2#.............#Isobaric processes\n",
+    "t4=t3*((p4/p3)**((gag-1)/gag))#............#Ideal temperature after expansion in turbine in K\n",
+    "t41=t3-(etat*(t3-t4))#.................#Actual temperature after expansion in turbine in K\n",
+    "wc=cp*(t21-t1)#................#Work dony by compressor\n",
+    "m1=(wc)/(cpg*(t3-t41))#.............#Flow through compressor turbine in kg\n",
+    "m2=1-m1#..............#Flow through power turbine in kg\n",
+    "wpt=m2*(cpg*(t3-t41))#.........#turbine work in kJ/kg\n",
+    "P=ma*wpt*etamech*etagen#.........#Power output in kW\n",
+    "qi=cpg*t3-cp*t21#.............#Input heat in kJ/kg of air\n",
+    "etath=wpt/qi#.............#Thermal efficiency of power turbine\n",
+    "print \"Thermal efficiency of power turbine = %0.2f %%\"%(etath*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 21.10 PAGE 854"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 8,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Temperature of gasses entering the turbine = 654.75 K\n",
+      "Pressure of gasses entering the power turbine = 1.65 bar\n",
+      "Net power output = 73.95 kW\n",
+      "Work ratio : 0.2198\n",
+      "Thermal efficiency of the unit : 19.26 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "# Initialisation of Variables\n",
+    "t1=288#........#Temperature of air entering the turbine in K\n",
+    "t3=883#..............#Temperature before expansion in turbine in K\n",
+    "etac=0.82#....#Efficiency of compressor\n",
+    "etathp=0.85#.....#Efficiency of high pressure turbine\n",
+    "etatlp=0.85#.....#Efficiency of low pressure turbine\n",
+    "rp=7#...........#Pressure ratio\n",
+    "p1=1.01#...............#Pressure of air before entering compressor\n",
+    "ga=1.4#........#Ratio of specific heats for compression\n",
+    "gag=1.333#........#Ratio of specific heats for expansion\n",
+    "cp=1.005#.............#Specific heat at constant pressure in kJ/kgK \n",
+    "cpg=1.15#.............#Specific heat at constant pressure in kJ/kgK in generator\n",
+    "#Calculations\n",
+    "p2=p1*rp#\n",
+    "t2=t1*((p2/p1)**((ga-1)/ga))#...............#Ideal temperature of air after compression in K\n",
+    "t21=((t2-t1)/etac)+t1#..............#Actual temperature of air after compression in K\n",
+    "wc=cp*(t21-t1)#............#Compressor work in kJ/kg\n",
+    "t41=t3-(wc/cpg)#..........#Temperature of gasses entering the turbine in K\n",
+    "print \"Temperature of gasses entering the turbine = %0.2f K\"%t41\n",
+    "t4=round(t3-((t3-t41)/etathp))#.........#Ideal temperature of gases entering the turbine in K\n",
+    "p3=p2#.........#Isobaric processes\n",
+    "p4=p3/((t3/t4)**(1/((gag-1)/gag)))#....#Pressure of gasses entering the power turbine in bar\n",
+    "print \"Pressure of gasses entering the power turbine = %0.2f bar\"%p4\n",
+    "t5=t41*((((t3/t4)**(1/((gag-1)/gag)))/(rp))**((gag-1)/gag))#\n",
+    "t51=t41-(etatlp*(t41-t5))#\n",
+    "wlp=cpg*(t41-t51)#............#Net power output in kW\n",
+    "print \"Net power output = %0.2f kW\"%wlp\n",
+    "wr=wlp/(wlp+wc)#............#Work ratio\n",
+    "print \"Work ratio : %0.4f\"%wr\n",
+    "qs=cpg*(t3-t21)#...........#Heat supplied in kJ/kg\n",
+    "etath=wlp/qs#..........#Thermal efficiency\n",
+    "print \"Thermal efficiency of the unit : %0.2f %%\"%(etath*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 21.11 PAGE 855"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 8,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Net work output = 173.98 kW\n",
+      "Power plant efficiency = 25.00 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from math import sqrt\n",
+    "# Initialisation of Variables\n",
+    "rp=5.6#................#Pressure ratio\n",
+    "t1=303#.............#Temperature of intake air in K\n",
+    "p1=1#............#Pressure of intake air in bar\n",
+    "t5=973#............#Highest temperature of the cycle in K\n",
+    "etac=0.85#..........#Effeciency of compressor\n",
+    "etat=0.9#..........#Efficiency of turbine\n",
+    "ma=1.2#..........#Rate of air flow in kg/s\n",
+    "cp=1.02#...........#Specific heat at constant volume in kJ/kgK\n",
+    "ga=1.41#.............#Ratio of specific heats\n",
+    "#Calculations\n",
+    "t2=t1*((sqrt(rp))**((ga-1)/ga))#\n",
+    "t21=((t2-t1)/etac)+t1#\n",
+    "wc=2*ma*cp*(t21-t1)#............#Work input for the two stage compressor in kJ/s\n",
+    "t6=t5/(rp**((ga-1)/ga))#\n",
+    "t61=t5-etat*(t5-t6)#\n",
+    "wt=ma*cp*(t5-t61)#...............#Work output from turbine in kJ/s\n",
+    "wnet=wt-wc#....................#Net work available in kJ/s\n",
+    "print \"Net work output = %0.2f kW\"%wnet\n",
+    "qs=ma*cp*(t5-t21)#.................#Heat supplied in kJ/s\n",
+    "etath=wnet/qs#\n",
+    "print \"Power plant efficiency = %0.2f %%\"%(etath*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 21.13 PAGE 856"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 9,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Cycle efficiency = 11.81 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "# Initialisation of Variables\n",
+    "t1=288#.............#Temperature of intake air in K\n",
+    "rp=4#.............#Pressure ratio\n",
+    "etac=0.82#.........#Compressor efficiency\n",
+    "etahe=0.78#...........#Efficiency of heat exchanger\n",
+    "etat=0.7#...........#Turbine efficiency\n",
+    "t3=873#............#Temperature before expansion in turbine in K\n",
+    "R=0.287#............#Gas constant for air in kJ/kgK\n",
+    "ga=1.4#...........#Ratio of specific heats\n",
+    "#Calculations\n",
+    "t2=t1*((rp)**((ga-1)/ga))#...............#Ideal temperature of air after compression in K\n",
+    "t21=((t2-t1)/etac)+t1#...............#Actual temperature of air after compression in K\n",
+    "t4=t3/(rp**((ga-1)/ga))#............#Ideal temperature after expansion in turbine in K\n",
+    "t41=t3-etat*(t3-t4)#............#Actual temperature after expansion in turbine in K\n",
+    "cp=R*(ga/(ga-1))#..............#Specific heat at constant pressure in kJ/kgK\n",
+    "wc=cp*(t21-t1)#.............#Compressor work in kJ/kg\n",
+    "wt=cp*(t3-t41)#....................#Turbine work in kJ/kg\n",
+    "wnet=wt-wc#....................#Net work available in kJ/s\n",
+    "t5=(etahe*(t41-t21))+t21#\n",
+    "qs=cp*(t3-t5)#.................#Heat supplied in kJ/kg\n",
+    "etac=wnet/qs#...............#Cycle efficiency\n",
+    "print \"Cycle efficiency = %0.2f %%\"%(etac*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 21.14 PAGE 857"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 10,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Thermal efficiency in simple cycle = 23.25 %\n",
+      "Thermal efficiency in heat exchanger cycle = 20.94 %\n",
+      "Increase in thermal efficiency = -2.31 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "# Initialisation of Variables\n",
+    "etahe=0.72#.................#Efficiency of heat exchanger\n",
+    "p1=1.01#.........#Pressure of air while entering the turbine in bar\n",
+    "t1=293#........#Temperature of air entering the turbine in K\n",
+    "p2=4.04#.........#Pressure of air after compression in bar\n",
+    "etat=0.85#..........#Turbine efficiency\n",
+    "pdhe=0.05#............#Pressure drop on each side of heat exchanger in bar\n",
+    "pdcc=0.14#...........#Pressure drop in combustion chamber in bar\n",
+    "etac=0.8#...........#Compressor efficiency\n",
+    "ga=1.4#.............#Ratio of specific heats\n",
+    "C=41800#.............#Calorific value of fuel in kJ/kg\n",
+    "cp=1.024#...........#Specific heat at constant pressure in kJ/kgK\n",
+    "afrc=90#..............#Air fuel ratio for simple cycle\n",
+    "#Calculations\n",
+    "t2=(t1*((p2/p1)**((ga-1)/ga)))#...............#Ideal temperature of air after compression in K\n",
+    "t21=round(((t2-t1)/etac)+t1)#...............#Actual temperature of air after compression in K\n",
+    "t3=((1*C)/(cp*(afrc+1)))+t21#............#Temperature before expansion in turbine in K\n",
+    "p4=p1#p3=p2-pdcc#t4=round(t3*((p4/p3)**((ga-1)/ga)))#............#Ideal temperature after expansion in turbine in K\n",
+    "t41=t3-(etat*(t3-t4))#.................#Actual temperature after expansion in turbine in K\n",
+    "etath=(t3-t41-t21+t1)/(t3-t21)#...........#Thermal efficiency in simple cycle\n",
+    "print \"Thermal efficiency in simple cycle = %0.2f %%\"%(etath*100)\n",
+    "p3he=p2-pdhe-pdcc#..........#Pressure before expansion in turbine in bar in heat exchanger cycle\n",
+    "p4he=p1+pdhe#................#Pressure after expansion in turbine in bar in heat exchanger cycle\n",
+    "t4he=t3*((p4he/p3he)**((ga-1)/ga))#............#Ideal temperature after expansion in turbine in K in heat exchanger cycle\n",
+    "t41he=round(t3-(etat*(t3-t4he)))#.................#Actual temperature after expansion in turbine in K in heat exchanger cycle\n",
+    "t5=(etahe*(t41he-t21))+t21#\n",
+    "etathhe=(t3-t41he-t21+t1)/(t3-t5)#.............#Thermal efficiency for heat exchanger cycle\n",
+    "print \"Thermal efficiency in heat exchanger cycle = %0.2f %%\"%(etathhe*100)\n",
+    "inc=etathhe-etath#\n",
+    "print \"Increase in thermal efficiency = %0.2f %%\"%(inc*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 21.15 PAGE 858"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 11,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Thermal efficiency = 23.44 %\n",
+      "The workk ratio is 0.283\n",
+      "Mass flow = 39.12 kg/s\n"
+     ]
+    }
+   ],
+   "source": [
+    "from math import sqrt\n",
+    "# Initialisation of Variables\n",
+    "t1=293#........#Temperature of air entering the turbine in K\n",
+    "rp=9#............#Overall pressure ratio\n",
+    "etac=0.8#........#Efficiency of compressor\n",
+    "t6=898#..........#Reheat remperature\n",
+    "t8=t6#etat=0.85#.......#Efficiency of turbine\n",
+    "etamech=0.95#..........#Mechanical efficiency\n",
+    "etahe=0.8#...............#Heat exchanger thermal efficiency\n",
+    "cpg=1.15#.............#Specific heat capacity for gases in heat exchanger in kJ/kgK\n",
+    "cpa=1.005#............#Specific heat capacity for normal air in kJ/kgK\n",
+    "gag=1.333#.............#Ratio of specific heats for gases in heat exchanger \n",
+    "ga=1.4#...............#Ratio of specific heats for normal gases\n",
+    "P=4500#.................#Power output of turbine in kW\n",
+    "#Calculations\n",
+    "t2=t1*((sqrt(rp))**((ga-1)/ga))#\n",
+    "t21=((t2-t1)/etac)+t1#\n",
+    "wc=cpa*(t21-t1)#............#Work input per compressor stage\n",
+    "whp=(2*wc)/etamech#.........#Work output of HP turbine in kJ/kg\n",
+    "t71=t6-(whp/cpg)#\n",
+    "t7=round(t6-((t6-t71)/etat))#\n",
+    "k=(rp/((t6/t7)**((gag)/(gag-1))))**((gag-1)/gag)#\n",
+    "k1=((round((k/2)*100))*2)/100#..............#Rounding off upto 2 decimals\n",
+    "t9=t8/(k1)#\n",
+    "t91=t8-((t8-t9)*etat)#\n",
+    "wout=cpg*(t8-t91)*etamech#..............#Net work output in kJ/kg\n",
+    "t5=etahe*(t91-t21)+t21#\n",
+    "qs=cpg*(t6-t5)+cpg*(t8-t71)#...............#Heat supplied\n",
+    "etath=wout/qs#.................#Thermal efficiency\n",
+    "print \"Thermal efficiency = %0.2f %%\"%(etath*100)\n",
+    "wgross=whp+(wout/etamech)#.........#Gross work output in kJ/kg\n",
+    "wr=wout/wgross#................#Work ratio\n",
+    "print \"The workk ratio is %0.3f\"%wr\n",
+    "m1=P/wout#...............#Mass flow in kg/s\n",
+    "print \"Mass flow = %0.2f kg/s\"%m1"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 21.16 PAGE 859"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 12,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Thermal efficiency of the turbine without regenerator = 27.01 %\n",
+      "Thermal efficiency of the turbine with regenerator = 38.96 %\n",
+      "Mass of fluid circulated = 2.40 kg/s\n"
+     ]
+    }
+   ],
+   "source": [
+    "from math import sqrt\n",
+    "# Initialisation of Variables\n",
+    "#Conditions of the closed gas turbine\n",
+    "t1=293#.............#Temperature at the inlet of first stage compressor in K\n",
+    "t5=1023#.................#Maximum temperature in K\n",
+    "p1=1.5#................#Inlet pressure in bar\n",
+    "p2=6#.................#Pressure in bar\n",
+    "etac=0.82#..............#Compressor efficiency\n",
+    "etat=0.82#..............#Turbine efficiency\n",
+    "etare=0.70#................#Regenerator efficiency\n",
+    "P=350#....................#Power developed by the plant in kW\n",
+    "ga=1.4#................#Ratio of specific heats\n",
+    "cp=1.005#..............#Specific heat at constant pressure in kJ/kgK\n",
+    "t3=t1#\n",
+    "#Calculations\n",
+    "t2=t1*((sqrt(p2/p1))**((ga-1)/ga))#\n",
+    "t21=((t2-t1)/etac)+t1#t41=t21#\n",
+    "t6=t5/((p2/sqrt(p1*p2))**((ga-1)/ga))#\n",
+    "t61=t5-(etat*(t5-t6))#\n",
+    "t81=t61#\n",
+    "t7=t5#\n",
+    "ta=(etare*(t81-t41))+t41#.......#Temperature of air coming out of regenerator in K\n",
+    "wnet=2*cp*(t5-t61-t21+t1)#........#Net work done in kJ/kg of air\n",
+    "qs=cp*(t5-t41+t7-t61)#...........#Heat supplied without regenerator in kJ/kg of air\n",
+    "qsr=cp*(t5-ta+t7-t61)#............#Heat supplied with regenerator in kJ/kg of air\n",
+    "etath=wnet/qs#.............#Thermal efficiency (without regenerator)\n",
+    "etathr=wnet/qsr#.........#Thermal efficiency (with regenerator)\n",
+    "mfl=P/wnet#..........#mass of fluid circulated in kg/s\n",
+    "print \"Thermal efficiency of the turbine without regenerator = %0.2f %%\"%(etath*100)\n",
+    "print \"Thermal efficiency of the turbine with regenerator = %0.2f %%\"%(etathr*100)\n",
+    "print \"Mass of fluid circulated = %0.2f kg/s\"%mfl"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 21.17 PAGE 860"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 13,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Net power output = 2042.40 kW \n",
+      "Thermal efficiency = 30.95 %\n",
+      "Specific fuel consumption = 0.28 kg/kWh\n"
+     ]
+    }
+   ],
+   "source": [
+    "# Initialisation of Variables\n",
+    "t1=293#............#Temperature of inlet air into low pressure compressor in K\n",
+    "p1=1.05#.........#Pressure of inlet air into low pressure compressor in bar\n",
+    "t3=300#...........#Temperature of air after passing it through intercooler in K\n",
+    "t6=1023#..........#temperature of air in combustion chamber in K\n",
+    "rp=2#...........#Pressure ratio of each compressor \n",
+    "etac=0.82#........#Compressor efficiency\n",
+    "etat=0.82#..........#Turbine efficiency\n",
+    "etaht=0.72#............#Heat exchanger efficiency\n",
+    "ma=16#...........#Air flow in kg/s\n",
+    "ga=1.4#...........#Ratio of specific heats for air\n",
+    "gag=1.33#..........#Ratio of specific heats for gases\n",
+    "cpa=1.0#...........#Specific heat at constant pressure in kJ/kgK for air\n",
+    "cpg=1.15#.........#Specific heat at constant pressure in kJ/kgK for gases\n",
+    "C=42000#.........#Calorific value of fuel in kJ/kg\n",
+    "#Calculations\n",
+    "t2=round(t1*(rp**((ga-1)/ga)))#\n",
+    "t21=round(((t2-t1)/etac)+t1)#\n",
+    "t4=t3*(rp**((ga-1)/ga))#\n",
+    "t41=round(((t4-t3)/etac)+t3)#\n",
+    "t71=round(((cpg*t6)-cpa*(t21-t1+t41-t3))/cpg)#\n",
+    "t7=t6-((t6-t71)/etat)#\n",
+    "p6=p1*rp*rp#\n",
+    "p7=p6/((t6/t7)**((gag)/(gag-1)))#\n",
+    "t8=round(t71/((p7/p1)**((gag-1)/gag)))#\n",
+    "t81=round(t71-(etat*(t71-t8)))#\n",
+    "P=cpg*(t71-t81)#...........#Net power output in kJ/kg\n",
+    "print \"Net power output = %0.2f kW \"%(P*ma)\n",
+    "t5=etaht*(t81-t41)+t41#\n",
+    "qs=ma*cpg*(t6-t5)#......#Heat supplied in combustion chamber in kJ/s\n",
+    "etath=P*ma/qs#.........#Thermal efficiency\n",
+    "print \"Thermal efficiency = %0.2f %%\"%(etath*100)\n",
+    "afr=C/(cpg*(t6-t5))#......#Air fuel ratio\n",
+    "mf=ma*3600/afr#..............#Fuel supplied per hour in kg\n",
+    "sfc=mf/(P*ma)#...........#Specific fuel consumption in kg/kWh\n",
+    "print \"Specific fuel consumption = %0.2f kg/kWh\"%sfc"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 21.18 PAGE 861"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 14,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Overall efficiency = 30.89 %\n",
+      "Work ratio  = 0.363  Mass flow rate = 34.32 kg/s\n"
+     ]
+    }
+   ],
+   "source": [
+    "# Initialisation of Variables\n",
+    "t1=293#............#Temperature of inlet air into low pressure compressor in K\n",
+    "p1=1.1#.........#Pressure of inlet air into low pressure compressor in bar\n",
+    "p2=3.3#..........#Pressure of air in the low pressure compressor in bar\n",
+    "t3=300#.............#Intercooled temperature in K\n",
+    "pli=0.15#..........#Loss in pressure due to intercooling in bar\n",
+    "p3=p2-pli#...........#Pressure after intercooling in bar\n",
+    "p4=9.45#............#Pressure of air after high pressure compressor in bar\n",
+    "p6=p4#t6=973#.........#Temperature of gases supplied to high pressure turbine in K\n",
+    "t8=943#.........#Reheat temperature in K\n",
+    "plr=0.12#...........#Loss of pressure after reheating in bar\n",
+    "p7=3.62#............#Pressure of gases at the end of expansion in high pressure turbine in bar\n",
+    "p8=p7-plr#...........#Pressure of outlet gases in bar\n",
+    "ga=1.4#...........#Ratio of specific heats for air\n",
+    "gag=1.33#..........#Ratio of specific heats for gases\n",
+    "cpa=1.005#...........#Specific heat at constant pressure in kJ/kgK for air\n",
+    "cpg=1.15#.........#Specific heat at constant pressure in kJ/kgK for gases\n",
+    "etac=0.82#........#Compressor efficiency\n",
+    "etat=0.85#..........#Turbine efficiency\n",
+    "etaht=0.65#.........#Efficiency of heat exchanger\n",
+    "P=6000#..................#Power generated in kW\n",
+    "p9=p1#\n",
+    "#Calculations\n",
+    "t2=round(t1*((p2/p1)**((ga-1)/ga)))#\n",
+    "t21=round(((t2-t1)/etac)+t1)#\n",
+    "t4=round(t3*((p4/p3)**((ga-1)/ga)))#\n",
+    "t41=round(((t4-t3)/etac)+t3)#\n",
+    "t7=round(t6/((p6/p7)**((gag-1)/gag)))#\n",
+    "t71=round(t6-(etat*(t6-t7)))#\n",
+    "t9=round(t8/((p8/p9)**((gag-1)/gag)))#\n",
+    "t91=round(t8-(etat*(t8-t9)))#\n",
+    "t5=round(etaht*(t91-t41)+t41)#\n",
+    "wthp=cpg*(t6-t71)#.......#Work done by high pressure turbine in kJ/kg of gas\n",
+    "wtlp=cpg*(t8-t9)#.......#Work done by low pressure turbine in kJ/kg of gas\n",
+    "wchp=cpg*(t21-t1)#.......#Work done by high pressure compressor in kJ/kg of gas\n",
+    "wclp=cpg*(t41-t3)#.......#Work done by low pressure compressor in kJ/kg of gas\n",
+    "qs=cpg*(t6-t5+t8-t71)#.........#Heat supplied in kJ/kg of gas\n",
+    "etath=(wthp+wtlp-wchp-wclp)/qs#..#Overall efficiency\n",
+    "print \"Overall efficiency = %0.2f %%\"%(etath*100)\n",
+    "wr=(wthp+wtlp-wchp-wclp)/(wthp+wtlp)#......#Work ratio\n",
+    "print \"Work ratio  = %0.3f \"%wr,\n",
+    "m=P/(wthp+wtlp-wchp-wclp)#.....#Mass flow rate\n",
+    "print \"Mass flow rate = %0.2f kg/s\"%m"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 21.19 PAGE 862"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 3,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Exit velocity of jet = 651.10 m/s\n",
+      "Rate of fuel consumption = 0.86 kg/s\n",
+      "Thrust specific fuel consumption = 0.00 kg/N\n",
+      "Thermal efficiency = 31.41 %\n",
+      "Propulsive power = 10437.94 kW\n",
+      "Propulsive efficiency = 59.81 %\n",
+      "Overall efficiency = 18.79 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt\n",
+    "# Initialisation of Variables\n",
+    "ma=60.2#...........#Rate of air consumption in kg/s\n",
+    "delh=230#.......#Enthalpy change for nozzle in kJ/kg\n",
+    "z=0.96#..........#Velocity co efficient \n",
+    "afr=70#............#Air fuel ratio\n",
+    "etaco=0.92#...............#Combustion eficiency\n",
+    "CV=42000#..............#Calorific value of fuel in kJ/kg\n",
+    "v=1000#............#Velocity of aircraft in km/h\n",
+    "Ca=v*(5/18)#............#Aircraft velocity in m/s\n",
+    "#Calculations\n",
+    "Cj=z*sqrt(2*delh*v)#...........#Exit velocity of jet\n",
+    "print \"Exit velocity of jet = %0.2f m/s\"%Cj\n",
+    "mf=ma/afr#.........#Rate of fuel consumption\n",
+    "print \"Rate of fuel consumption = %0.2f kg/s\"%mf\n",
+    "tp=ma*(Cj-Ca)#......#Thrust produced in N\n",
+    "tsfc=mf/tp#.........#Thrust specific fuel consumption in kg/N\n",
+    "print \"Thrust specific fuel consumption = %0.2f kg/N\"%tsfc\n",
+    "etath=((Cj**2)-(Ca**2))/(2*(1/afr)*CV*etaco*1000)#.........#Thermal efficiency\n",
+    "print \"Thermal efficiency = %0.2f %%\"%(etath*100)\n",
+    "pp=(ma/1000)*((Cj**2)-(Ca**2))/2#................#Propulsive power in kW\n",
+    "print \"Propulsive power = %0.2f kW\"%pp\n",
+    "etapp=(2*Ca)/(Cj+Ca)#......................#Propulsive efficiency\n",
+    "print \"Propulsive efficiency = %0.2f %%\"%(etapp*100)\n",
+    "etao=((Cj-Ca)*Ca)/((1/afr)*CV*etaco*1000)#............#Overall efficiency\n",
+    "print \"Overall efficiency = %0.2f %%\"%(etao*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 21.20 PAGE 863"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 16,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Absolute velocity of jet = 363.64 m/s\n",
+      "Volume of air compressed = 5920.59 kg/min\n",
+      "Diameter of the jet = 463.09 mm\n",
+      "Turbine output = 2464.65 kW\n",
+      "\n",
+      "Air fuel ratio is 53.225:1\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi,sqrt\n",
+    "# Initialisation of Variables\n",
+    "v=800#.............#Speed of the turbojet in km/h\n",
+    "etapp=0.55#......#Propulsive efficiency\n",
+    "etao=0.17#.........#Overall efficiency\n",
+    "al=9500#...............#Altitude in m\n",
+    "rhoa=0.17#............#Density of air at the given altitude in kg/m**3\n",
+    "dr=6100#...........#Drag on the plane in N\n",
+    "CV=46000#.........#Calorific value of fuel in kJ/kg\n",
+    "#Calculations\n",
+    "Ca=v*(1000/3600)#.........#Velocity of jet in m/s\n",
+    "Cj=((2*Ca)/etapp)-Ca#........#Velocity of gases at nozzle exit relative to the aircraft in m/s\n",
+    "print \"Absolute velocity of jet = %0.2f m/s\"%(Cj-Ca)\n",
+    "ma=dr/(Cj-Ca)#............#Rate of air flow in kg/s\n",
+    "Va=(ma/rhoa)*60#..........#Volume of air compresssed per min in kg\n",
+    "print \"Volume of air compressed = %0.2f kg/min\"%Va\n",
+    "d=sqrt((Va*4)/(60*pi*Cj))#..........#Diameter of the jet in m\n",
+    "print \"Diameter of the jet = %0.2f mm\"%(d*1000)\n",
+    "tp=dr*(Ca/1000)#...........#Thrust power in kW\n",
+    "wt=tp/etapp#................#Turbine output in kW\n",
+    "print \"Turbine output = %0.2f kW\"%wt\n",
+    "mf=wt/(etao*CV)#...........#Rate of fuel consumption in kg/s\n",
+    "afr=ma/mf#..........#Air fuel ratio\n",
+    "print \"\\nAir fuel ratio is %0.3f:1\"%(afr)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 21.21 PAGE 864"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 17,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Power required to drive the compressor = 171.46 kW\n",
+      "\n",
+      "\n",
+      "Air fuel ratio 73.094:1\n",
+      "\n",
+      "Pressure of gases leaving the turbine = 1.74 bar\n",
+      "Thrust per kg of air per second = 465.69 N\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi,sqrt\n",
+    "# Initialisation of Variables\n",
+    "t1=288#..........#Temperature of the inlet air into compressor in K\n",
+    "p1=1.01#......#Pressure of the inlet air into compressor in bar\n",
+    "t3=1023#.........#Maximum temperature in K\n",
+    "p2=4.04#.........#Pressure of air at the end of compression in bar\n",
+    "etac=0.82#.......#compressor efficiency\n",
+    "etat=0.78#......#Turbine efficiency\n",
+    "etan=0.88#........#Nozzle efficiency\n",
+    "R=0.287#.........#Gas constant for air in kJ/kgK\n",
+    "ga=1.4#............#Ratio of specific heats\n",
+    "C=42000#..........#Calorific value of fuel in kJ/kg\n",
+    "#Calculations\n",
+    "t2=t1*((p2/p1)**((ga-1)/ga))#........#Ideal temperature at the end of compression in K\n",
+    "t21=((t2-t1)/etac)+t1#...........#Actual temperature at the end of compression in K\n",
+    "cp=R*(ga/(ga-1))#..............#Specific heat at constant pressure in kJ/kgK\n",
+    "Pc=cp*(t21-t1)#.............#Power required to drive the compressor in kW\n",
+    "print \"Power required to drive the compressor = %0.2f kW\"%Pc\n",
+    "afr=((C)/(cp*(t3-t21)))-1#....#Air fuel ratio\n",
+    "print \"\\n\\nAir fuel ratio %0.3f:1\\n\"%(afr)\n",
+    "t41=t1+t3-t21#......#Actual temperatur of gases leaving the turbine in K\n",
+    "t4=t3-((t3-t41)/etat)#......#Ideal temperature of gases leaving the turbine in K\n",
+    "p3=p2#\n",
+    "p4=p3*((t4/t3)**(ga/(ga-1)))#.......#Pressure of gases leaving the turbine in bar\n",
+    "print \"Pressure of gases leaving the turbine = %0.2f bar\"%p4\n",
+    "p5=p1#\n",
+    "t5=t41/((p4/p5)**((ga-1)/ga))#\n",
+    "t51=t41-(etan*(t41-t5))#\n",
+    "Cj=sqrt(2*cp*(t41-t51)*1000)#..............#Jet velocity in m/s\n",
+    "th=Cj*1#..................#Thrust per kg per second in N\n",
+    "print \"Thrust per kg of air per second = %0.2f N\"%th"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 21.22 PAGE 865"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 18,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Air fuel ratio : 48.348\n",
+      "Specific thrust = 822.74 N/kg\n",
+      "Total thrust = 21805.03 N\n"
+     ]
+    }
+   ],
+   "source": [
+    "from scipy import sqrt\n",
+    "# Initialisation of Variables\n",
+    "Ca=216#................#Speed of aircraft in m/s\n",
+    "t1=265.8#...............#Intake air temperature in K\n",
+    "p1=0.78#...............#Intake air pressure in bar\n",
+    "rp=5.8#..................#Pressure ratio in compressor \n",
+    "t4=1383#.................#Temperature of gases entering the gas turbine in K\n",
+    "pd=0.168#...............#Pressure drop in combustion chamber in bar\n",
+    "etad=0.9#..............#Diffuser efficiency\n",
+    "etan=0.9#............#Nozzle efficiency\n",
+    "etac=0.9#............#Compressor efficiency\n",
+    "etat=0.8#.............#Turbine efficiency\n",
+    "C=44150#............#Calorific value of fuel in kJ/kg\n",
+    "cp=1.005#.............#Specific heat at constant pressure in kJ/kgK\n",
+    "ga=1.4#...............#Ratio of specific heats\n",
+    "cin=0.12#...............#Inlet cross sectio of the diffuser in m**3\n",
+    "R=0.287#............#Gas constant in kJ/kgK\n",
+    "#Calculations\n",
+    "t2=t1+((Ca*Ca)/(2*cp*1000))#......#For ideal diffuser\n",
+    "t21=t1+((Ca*Ca)/(2*cp*etad*1000))#......#For actual diffuser\n",
+    "p2=p1*((t2/t1)**(ga/(ga-1)))#\n",
+    "t3=t21*(rp**((ga-1)/ga))#\n",
+    "t31=t21+((t3-t21)/etac)#\n",
+    "afr=(C-(cp*t4))/(cp*(t4-t31))#............#Air fuel ratio\n",
+    "print \"Air fuel ratio : %0.3f\"%afr\n",
+    "p3=p2*rp#\n",
+    "p4=p3-pd#...............#Pressure of gases entering the turbine in bar\n",
+    "t51=t4-(t31-t21)#\n",
+    "t5=round(t4-((t4-t51)/etat))#\n",
+    "p5=p4/((t4/t5)**(ga/(ga-1)))#\n",
+    "p6=p1#\n",
+    "t6=t51/((p5/p6)**((ga-1)/ga))#\n",
+    "t61=t51-(etac*(t51-t6))#\n",
+    "Cj=44.72*sqrt(cp*(t51-t61))#........#Velocity at the exit of the nozzle in m/s\n",
+    "st=(1+(1/afr))*Cj#............#Specific thrust in N/kg\n",
+    "print \"Specific thrust = %0.2f N/kg\"%abs(st)\n",
+    "v1=Ca*cin#...........#Volume of flowing air in m**3/s\n",
+    "ma=(p1*v1*10**5)/(R*t1*1000)#.........#Mass flow of air\n",
+    "tt=ma*st#..............#Total thrust in N\n",
+    "print \"Total thrust = %0.2f N\"%abs(tt)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 21.23 PAGE 866"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 1,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Overall efficiency = 12.91 %\n",
+      "Rate of air consumption = 9.23 kg/s\n",
+      "Power developed by turbine = 1496.76 kW\n",
+      "The outlet area of jet tube = 0.10 m**2\n",
+      "Specific fuel consumption = 0.16 kg per kg of thrust\n"
+     ]
+    }
+   ],
+   "source": [
+    "from math import sqrt\n",
+    "# Initialisation of Variables\n",
+    "al=9000#..........#Altitude in m\n",
+    "Ca=215#...........#Speed of aircraft in m/s\n",
+    "TP=750#.............#Thrust power developed in kW\n",
+    "p1=0.32#...........#Inlet pressure of air in bar\n",
+    "t1=231#.............#Inlet temperature of air in K\n",
+    "t3=963#.............#Temperature of gases leaving the combustion chamber in K\n",
+    "rpc=5.2#............#Pressure ratio\n",
+    "C=42500#..........#Calorific value of fuel in kJ/kg\n",
+    "C41=195#.........#Velocity in ducts\n",
+    "etac=0.86#..........#Compressor efficiency\n",
+    "ga=1.4#............#Ratio of specific heats for air\n",
+    "gag=1.33#............#Ratio of specific heats for gases\n",
+    "etat=0.86#..........#Turbine efficiency\n",
+    "etajt=0.9#..........#Jet tube efficiency\n",
+    "cp=1.005#............#Specific heat at constant pressure in kJ/kgK for air\n",
+    "cpg=1.087#............#Specific heat at constant pressure in kJ/kgK for gases\n",
+    "R=0.29#..................#Gas constant for exhaust gases in kJ/kgK\n",
+    "#Calculations\n",
+    "t2=t1*(rpc**((ga-1)/ga))#\n",
+    "t21=t1+((t2-t1)/etac)#\n",
+    "mf=(cpg*(t3-t21))/(C-(cpg*(t3-t21)))#\n",
+    "afr=1/mf#..........#Air fuel ratio\n",
+    "t41=round(t3-((cp*(t21-t1))/(cpg*(1+mf))))#\n",
+    "t4=t3-((t3-t41)/etat)#\n",
+    "p4=rpc#\n",
+    "rpt=(t3/t4)**(gag/(gag-1))#.............#Expansion pressure ratio in turbine\n",
+    "rpj=p4/rpt#....................#Expansion pressure ratio in jet tube\n",
+    "t5=t41/(rpj**((gag-1)/gag))#\n",
+    "Cj=sqrt(etajt*2*((cpg*1000*(t41-t5))+((C41*C41)/2)))#\n",
+    "etao=((((1+mf)*Cj)-Ca)*Ca)/(1000*mf*C)#......#Overall efficiency\n",
+    "print \"Overall efficiency = %0.2f %%\"%(etao*100)\n",
+    "ma=(TP*1000)/((((1+mf)*Cj)-Ca)*Ca)#........#Rate of air consumption in kg/s\n",
+    "print \"Rate of air consumption = %0.2f kg/s\"%ma\n",
+    "P=ma*(1+mf)*cpg*(t3-t41)#..............#Power developed by the turbine in kW\n",
+    "print \"Power developed by turbine = %0.2f kW\"%P\n",
+    "t51=t41-(((Cj**2)-(C41**2))/(2*1000*cpg))#\n",
+    "rhoe=(p1*10**5)/(R*1000*t51)#..........#Density of exhaust gases\n",
+    "Ajt=(ma*(1+mf))/(Cj*rhoe)#.......#Discharge of jet area in m**2\n",
+    "print \"The outlet area of jet tube = %0.2f m**2\"%Ajt\n",
+    "sfc=(mf*ma*3600)/(1000*(TP/Ca))#..........#Specific fuel consumption in kg/thrust-hour\n",
+    "print \"Specific fuel consumption = %0.2f kg per kg of thrust\"%sfc"
+   ]
+  }
+ ],
+ "metadata": {
+  "kernelspec": {
+   "display_name": "Python 2",
+   "language": "python",
+   "name": "python2"
+  },
+  "language_info": {
+   "codemirror_mode": {
+    "name": "ipython",
+    "version": 2
+   },
+   "file_extension": ".py",
+   "mimetype": "text/x-python",
+   "name": "python",
+   "nbconvert_exporter": "python",
+   "pygments_lexer": "ipython2",
+   "version": "2.7.9"
+  }
+ },
+ "nbformat": 4,
+ "nbformat_minor": 0
+}
diff --git a/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER3_2.ipynb b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER3_2.ipynb
new file mode 100644
index 00000000..2eca0c90
--- /dev/null
+++ b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER3_2.ipynb
@@ -0,0 +1,1877 @@
+{
+ "cells": [
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "# CHAPTER 3 - Air Standard Cycles"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.1 PAGE 87"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 5,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Engine thermal efficiency = 53.49  %\n",
+      "Head added = 243.03 kJ\n",
+      "Change in entropy = 0.361 kJ/K\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "t1=673#.....................#Max temp in Kelvin\n",
+    "t3=313##...................#Min temp in Kelvin\n",
+    "W=130#.................#Work produced in kJ\n",
+    "#calculations\n",
+    "etath=(t1-t3)/t1#................#Engine thermal efficiency\n",
+    "print \"Engine thermal efficiency = %0.2f  %%\"%(etath*100)\n",
+    "ha=W/etath#.................#Heat added in kJ\n",
+    "print \"Head added = %0.2f kJ\"%ha\n",
+    "dels=(ha-W)/t3#...........#Change in entropy\n",
+    "print \"Change in entropy = %0.3f kJ/K\"%dels"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.2 PAGE 88"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 6,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The maximum temperature = 585.37 Kelvin\n",
+      "The minimum temperature = 292.68 Kelvin\n",
+      "Volume at the end of isothermal expansion = 0.19 m**3\n",
+      "\n",
+      "\n",
+      "\n",
+      "Process                                     Heat transfer\n",
+      "\n",
+      "_______________________________________________________________\n",
+      "\n",
+      "Isothermal expansion                               40 kJ\n",
+      "\n",
+      "Adiabatic reversible expansion                     0 kJ\n",
+      "\n",
+      "Isothermal compression                            -40 kJ\n",
+      "\n",
+      "Adiabatic reversible compressions                  0 kJ\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "m=0.5#.....................#Mass of air in kg\n",
+    "etath=0.5#.................#Thermal efficiency of engine\n",
+    "hie=40#...................#Heat transferred during isothermal expansion in kJ\n",
+    "p1=7#....................#Pressure in bar at the beginning of expansion\n",
+    "v1=0.12#..................#Volume in m**3 at the beginning of expansion\n",
+    "cv=0.721#...................#Specific heat at constant volume in kJ/kgK\n",
+    "cp=1.008#..................#Specific heat at constant pressure in kJ/kgK\n",
+    "R=287#......................#Gas constant in J/kgK\n",
+    "#Calculations\n",
+    "t1=(p1*10**5*v1)/(R*m)#....................#Max temp in K\n",
+    "t2=t1*(1-etath)#.......................#Min temp in K\n",
+    "print \"The maximum temperature = %0.2f Kelvin\"%t1\n",
+    "print \"The minimum temperature = %0.2f Kelvin\"%t2\n",
+    "from math import exp\n",
+    "v2=(exp((hie*1000)/(m*R*t1)))*v1#..................#Volume at the end of isothermal expansion in m**3\n",
+    "print \"Volume at the end of isothermal expansion = %0.2f m**3\"%v2\n",
+    "print \"\\n\\n\"\n",
+    "print \"Process                                     Heat transfer\\n\"\n",
+    "print \"_______________________________________________________________\\n\"\n",
+    "print \"Isothermal expansion                               %d kJ\\n\"%(hie)\n",
+    "print \"Adiabatic reversible expansion                     %d kJ\\n\"%(0)\n",
+    "print \"Isothermal compression                            %d kJ\\n\"%(-hie)\n",
+    "print \"Adiabatic reversible compressions                  %d kJ\"%(0)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.3 PAGE 89"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 7,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "p1=18 bar \n",
+      "p2=12 bar \n",
+      "p3=0.977 bar \n",
+      "p4=1.465 bar \n",
+      "t1=t2=683 Kelvin \n",
+      "t3=t4=334 Kelvin \n",
+      "\n",
+      "Change in entropy = 0.19 kJ/K\n",
+      "Mean effective pressure of the cycle = 0.47 bar\n",
+      "Mean effective pressure of the cycle = 235.25 bar\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import log\n",
+    "# Initialisation of Variables\n",
+    "p1=18#..................#Maximum pressure in bar\n",
+    "t1=410+273#.............#Maximum temperature in Kelvin\n",
+    "ric=6#.....................#Ratio of isentropic compression\n",
+    "rie=1.5#.................#Ratio of isothermal expansion\n",
+    "v1=0.18#..................#Volume of air at the beginning of expansion\n",
+    "ga=1.4#...................#Degree of freedom of gas\n",
+    "R=287#.....................#Gas constant in J/kgK\n",
+    "nc=210#..................#no of working cycles\n",
+    "#Calculations\n",
+    "\n",
+    "t4=t1/(ric**(ga-1))#.............#Min temp in K\n",
+    "t3=t4#\n",
+    "p4=p1/(ric**ga)#..................#Min pressure in bar\n",
+    "p2=p1/rie#.......................#pressure of gas before isentropic expansion in bar\n",
+    "p3=p2*((1/6)**ga)#.................#Pressure of gas after isentropic expansion in bar\n",
+    "print \"p1=%.f bar \\np2=%.f bar \\np3=%.3f bar \\np4=%.3f bar \\nt1=t2=%0.f Kelvin \\nt3=t4=%.f Kelvin \\n\"%(p1,p2,p3,p4,t1,t3)\n",
+    "dels=(p1*10**5*v1*log(rie))/(1000*t1)#....................#Change in entropy\n",
+    "print \"Change in entropy = %0.2f kJ/K\"%dels\n",
+    "qs=t1*dels#.......................#Heat supplied in kJ\n",
+    "Qr=t4*dels#.......................#Heat rejected in kJ\n",
+    "eta=(qs-Qr)/qs#............#Efficiency of the cycle\n",
+    "v3byv1=ric*rie#\n",
+    "Vs=(v3byv1-1)*v1#.................#Stroke volume\n",
+    "pm=((qs-Qr)*10**3)/(Vs*10**5)#........#Mean effective pressure of the cycle in bar\n",
+    "print \"Mean effective pressure of the cycle = %0.2f bar\"%pm\n",
+    "P=(qs-Qr)*(nc/60)#.........................#Power of engine\n",
+    "print \"Mean effective pressure of the cycle = %0.2f bar\"%P"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.4 PAGE 92"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 1,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Temperature of the sink = 1442 Celsius\n",
+      "temperature of source = 1785 Celsius:\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "eta=1/6#...................#Efficiency of the engine\n",
+    "rts=70#.................#The amount of temp which is reduced in the sink in C\n",
+    "#Calculation\n",
+    "t1byt2=1/(1-eta)#\n",
+    "t2=(rts+273)/((2*eta*t1byt2)-t1byt2+1)#............#Temperature of the sink in K\n",
+    "print \"Temperature of the sink = %0.f Celsius\"%(t2-273)\n",
+    "t1=t1byt2*t2#...............#Temperature of source in K\n",
+    "print \"temperature of source = %0.f Celsius:\"%(t1-273)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.5 PAGE 92"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 2,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Since the efficiency of the given engine is more than efficiency of carnot engine, the claim is not true.\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "t1=1990#....................#Temperature of the heat source in K\n",
+    "t2=850#..................#Temperature of the sink in K\n",
+    "Q=32.5#...................#Heat supplied in kJ/min\n",
+    "P=0.4#....................#Power developed by the engine in kW\n",
+    "#Calculations\n",
+    "eta=1-(t2/t1)#..........#Efficiency of carnot engine\n",
+    "etath=P/(Q/60)#..................#Efficiency of the given engine\n",
+    "if (etath>eta):\n",
+    "    print \"Since the efficiency of the given engine is more than efficiency of carnot engine, the claim is not true.\"\n"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.7 PAGE 96"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 3,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The compression ratio of the engine is: 6.25\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "etaotto=0.6#............#Efficiency of otto engine\n",
+    "ga=1.5#.................#Ratio of specific heats\n",
+    "#Calculations\n",
+    "r=(1/(1-etaotto))**(1/(ga-1))#................#Compression ratio\n",
+    "print \"The compression ratio of the engine is:\",r"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.8 PAGE 96"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 4,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The air standard efficiency of otto cycle = 56.47 %\n",
+      "Mean effective pressure = 1.34 bar\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "D=0.25#......................#Engine bore in m\n",
+    "L=0.375#...................#Engine stroke in m\n",
+    "Vc=0.00263#................#Clearence volume in m**3\n",
+    "p1=1#..................#Initial pressure in bar\n",
+    "t1=323#...................#Initial temperature in K\n",
+    "p3=25#....................#Max pressure in bar\n",
+    "ga=1.4#....................#Ratio of specific heats\n",
+    "#Calculations\n",
+    "Vs=(pi/4)*D*D*L#................#Swept volume in m**3\n",
+    "r=round((Vs+Vc)/Vc)#..........................#Compression ratio\n",
+    "etaotto=1-(1/(r**(ga-1)))#..................#Air standard efficiency of otto cycle\n",
+    "print \"The air standard efficiency of otto cycle = %0.2f %%\"%(etaotto*100)\n",
+    "p2=p1*((r)**ga)#\n",
+    "rp=p3/p2#..........................#Pressure ratio\n",
+    "pm=(p1*r*((r**(ga-1))-1)*(rp-1))/((ga-1)*(r-1))#................#Mean effective pressure in bar\n",
+    "print \"Mean effective pressure = %0.2f bar\"%pm"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.9 PAGE 98"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 12,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Temperature after adiabatic compression = 689.22 K\n",
+      "Pressure after adiabatic compression = 18.38 bar\n",
+      "Temperature after isochoric compression = 2772.55 K\n",
+      "Pressure after isochoric compression = 73.93 bar\n",
+      "Temperature after adiabatic expansion = 1206.82 K\n",
+      "Pressure after adiabatic expansion = 4.02 bar\n",
+      "Specific work = 847.09 kJ/kg\n",
+      "Thermal efficiency = 56.47 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "p1=1#.....................#Pressure in bar\n",
+    "t1=300#......................#Temperature in K\n",
+    "Q=1500#.....................#Heat added in kJ/kg\n",
+    "r=8#.......................#Compression ratio\n",
+    "Cv=0.72#....................#Specific heat at constant volume\n",
+    "ga=1.4#......................#Ratio of specific heats\n",
+    "#Calculations\n",
+    "t2=t1*(r)**(ga-1)#..........#Temperature after adiabatic compression in K\n",
+    "p2=p1*(r**ga)#..............#Pressure after adiabatic compression in bar\n",
+    "t3=(Q/Cv)+t2#.................#Temperature after isochoric compression in K\n",
+    "p3=(p2*t3)/t2#................#Pressure after isochoric compression in bar\n",
+    "t4=t3/(r**(ga-1))#.......................#Temperature after adiabatic expansion in K\n",
+    "p4=p3*(1/(r**(ga)))#................#Pressure after adiabatic expansion in bar\n",
+    "Ws=Cv*(t3-t2-t4+t1)#.........#Specific work in kJ/kg\n",
+    "etath=1-(1/(r**(ga-1)))#............#Thermal efficiency\n",
+    "print \"Temperature after adiabatic compression = %0.2f K\"%t2\n",
+    "print \"Pressure after adiabatic compression = %0.2f bar\"%p2\n",
+    "print \"Temperature after isochoric compression = %0.2f K\"%t3\n",
+    "print \"Pressure after isochoric compression = %0.2f bar\"%p3\n",
+    "print \"Temperature after adiabatic expansion = %0.2f K\"%t4\n",
+    "print \"Pressure after adiabatic expansion = %0.2f bar\"%p4\n",
+    "print \"Specific work = %0.2f kJ/kg\"%Ws\n",
+    "print \"Thermal efficiency = %0.2f %%\"%(etath*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.10 PAGE 99"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 13,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Temperature after adiabatic compression = 614.30 K\n",
+      "Pressure after adiabatic compression = 12.29 bar\n",
+      "Temperature after isochoric compression = 1842.00 K\n",
+      "Pressure after isochoric compression = 36.84 bar\n",
+      "Temperature after adiabatic expansion = 899.56 K\n",
+      "Pressure after adiabatic expansion = 3.00 bar\n",
+      "Thermal efficiency = 56.47 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "r=6#..............#Compression ratio\n",
+    "p1=1#................#Pressure after isochoric expansion in bar\n",
+    "t1=300#................#Temperature after isochoric expansion in K\n",
+    "t3=1842#...............#Temperature after isochoric compression in K\n",
+    "ga=1.4#...............#Ratio of specific heats\n",
+    "#Calculations\n",
+    "p2=p1*(r**ga)#...............#Pressure after adiabatic compression in bar\n",
+    "t2=t1*(r**(ga-1))#.............#Temperature after adiabatic compression in K\n",
+    "p3=p2*(t3/t2)#..................#pressure after isochoric compression in bar\n",
+    "t4=t3/(r**(ga-1))#..............#Temperature after adiabatic expansion in K\n",
+    "p4=p3*(1/(r**(ga)))#...........#Pressure after adiabatic expansion in bar\n",
+    "etaotto=1-(1/(r**(ga-1)))#............#Efficiency of otto cycle\n",
+    "p5=p1#\n",
+    "t5=((p5/p3)**((ga-1)/ga))*t3#................#Atkinson cycle temp after further adiabatic expansion in K\n",
+    "etatk=1-((ga*(t5-t1))/(t3-t2))#...........#Efficiency of atkinson cycle\n",
+    "print \"Temperature after adiabatic compression = %0.2f K\"%t2\n",
+    "print \"Pressure after adiabatic compression = %0.2f bar\"%p2\n",
+    "print \"Temperature after isochoric compression = %0.2f K\"%t3\n",
+    "print \"Pressure after isochoric compression = %0.2f bar\"%p3\n",
+    "print \"Temperature after adiabatic expansion = %0.2f K\"%t4\n",
+    "print \"Pressure after adiabatic expansion = %0.2f bar\"%p4\n",
+    "print \"Thermal efficiency = %0.2f %%\"%(etath*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.11 PAGE 101"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 1,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Compression ratio: 3.95\n",
+      "Temperature at the end of compression = 607.79 K\n",
+      "Temperature at the end of heat addition = 1266.43 K\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "p1=1#...................#Initial pressure in bar\n",
+    "t1=343#..................#Initial temperature in K\n",
+    "p2=7#....................#Pressure after adiabatic compression\n",
+    "Qs=465#...............#Heat addition at constant volume in kJ/kg\n",
+    "cp=1#.....................#Specific heat at constant pressure in kJ/kg\n",
+    "cv=0.706#..................#Specific heat at constant volume in kJ/kg\n",
+    "ga=cp/cv#.................#Ratio of specific heats\n",
+    "#Calculations\n",
+    "r=(p2/p1)**(1/ga)#...............#Compression ratio\n",
+    "t2=t1*(r**(ga-1))#.....................#Temperature at the end of compression in K\n",
+    "t3=t2+(Qs/cv)#.............#Temperature at the end of heat addition in K\n",
+    "print \"Compression ratio:\",round(r,2)\n",
+    "print \"Temperature at the end of compression = %0.2f K\"%t2\n",
+    "print \"Temperature at the end of heat addition = %0.2f K\"%t3"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.12 PAGE 102"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 2,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Compression ratio: 6.92\n",
+      "Thermal efficiency = 53.87 %\n",
+      "Work done = 598.65 kJ\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "ga=1.4#..............#Ratio of specific heats\n",
+    "p2byp1=15#...............#Ratio pressure at the end of compression to that of pressure at the start\n",
+    "t1=311#................#Initial temperature in K\n",
+    "t3=2223#...............#Maximum temperature in K\n",
+    "R=0.287#...............#Gas constant in kJ/kg K\n",
+    "#Calculations\n",
+    "r=p2byp1**(1/ga)#...............#Compression ratio\n",
+    "etath=1-(1/(r**(ga-1)))#.............#Thermal efficiency\n",
+    "t2=t1*(r**(ga-1))#............#Temperature at the end of compression in K\n",
+    "t4=t3/(r**(ga-1))#...........#Temperature at the end of isothermal expansion in K\n",
+    "cv=R/(ga-1)#................#Specific heat at constant volume in kJ/kg\n",
+    "Q=cv*(t3-t2)#..............#Heat supplied in kJ/kg of air\n",
+    "Qr=cv*(t4-t1)#.................#Heat rejected in kJ/kg of air\n",
+    "W=Q-Qr#.................#Work done\n",
+    "print \"Compression ratio:\",round(r,2)\n",
+    "print \"Thermal efficiency = %0.2f %%\"%(etath*100)\n",
+    "print \"Work done = %0.2f kJ\"%W"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.13 PAGE 104"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 3,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Temperature after adiabatic compression: 601.15 K\n",
+      "\n",
+      "Pressure after adiabatic compression: 11.00 bar\n",
+      "\n",
+      "Volume after adiabatic compression: 0.08 m**3\n",
+      "\n",
+      "Temperature after isochoric compression: 1172.73 K\n",
+      "\n",
+      "Pressure after isochoric compression: 21.46 bar\n",
+      "\n",
+      "Volume after isochoric compression: 0.08 m**3\n",
+      "\n",
+      "Temperature after adiabatic expansion: 591.09 K\n",
+      "\n",
+      "Pressure after adiabatic expansion: 1.95 bar\n",
+      "\n",
+      "Volume after adiabatic expansion: 0.45 m**3\n",
+      "\n",
+      "Percentage clearance: 22.01\n",
+      "\n",
+      "Efficiency of otto cycle: 49.60\n",
+      "\n",
+      "Mean effective pressure: 2.82 bar:\n",
+      "\n",
+      "Power developed: 364.54 kW\n",
+      "\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "v1=0.45#.............#Initial volume in m**3 \n",
+    "p1=1#...............#Initial pressure in bar\n",
+    "t1=303#.............#Initial temperature in K\n",
+    "p2=11#...................#Pressure at the end of compression stroke in bar\n",
+    "Q=210#...................#heat added at constant volume in kJ\n",
+    "N=210#.................#No of working cycles per min\n",
+    "ga=1.4#.............#Ratio of specific heats\n",
+    "R=287#.................#Gas constant in kJ/kgK\n",
+    "cv=0.71#.................#Specific heat at constant volume in kJ/kg\n",
+    "#Calculations\n",
+    "r=(p2/p1)**(1/ga)#...................#Compression ratio\n",
+    "t2=t1*(r**(ga-1))#...................#Temperature at the end of adiabatic compression\n",
+    "v2=(t2*p1*v1)/(t1*p2)#.................#Volume at the end of adiabatic compression in m**3\n",
+    "m=(p1*v1*10**5)/(R*t1)#................#Mass of engine fluid in kg\n",
+    "t3=(Q/(m*cv))+t2#...................#Temperature at the end of isochoric compression in K\n",
+    "p3=(t3/t2)*p2#................#Pressure at the end of isochoric compression in bar\n",
+    "v3=v2#\n",
+    "t4=t3*(1/r)**(ga-1)#...................#Temperature at the end of adiabatic expansion in K\n",
+    "p4=p3*(1/r)**ga#......................#Pressure at the end of adiabatic expansion in bar\n",
+    "v4=v1#\n",
+    "pc=(v2*100)/(v1-v2)#..................#Percentage clearence\n",
+    "etaotto=1-(1/(r**(ga-1)))#........................#Efficiency of otto cycle\n",
+    "Qr=m*cv*(t4-t1)#...............................#Heat rejected in kJ/kg\n",
+    "pm=((Q-Qr)*1000)/((v1-v2)*100000)#......#Mean effective pressure in bar\n",
+    "P=(Q-Qr)*(N/60)#........................#Power developed in kW\n",
+    "print \"Temperature after adiabatic compression: %0.2f K\\n\"%(t2)\n",
+    "print \"Pressure after adiabatic compression: %0.2f bar\\n\"%(p2)\n",
+    "print \"Volume after adiabatic compression: %0.2f m**3\\n\"%(v2)\n",
+    "print \"Temperature after isochoric compression: %0.2f K\\n\"%(t3)\n",
+    "print \"Pressure after isochoric compression: %0.2f bar\\n\"%(p3)\n",
+    "print \"Volume after isochoric compression: %0.2f m**3\\n\"%(v3)\n",
+    "print \"Temperature after adiabatic expansion: %0.2f K\\n\"%(t4)\n",
+    "print \"Pressure after adiabatic expansion: %0.2f bar\\n\"%(p4)\n",
+    "print \"Volume after adiabatic expansion: %0.2f m**3\\n\"%(v4)\n",
+    "print \"Percentage clearance: %0.2f\\n\"%(pc)\n",
+    "print \"Efficiency of otto cycle: %0.2f\\n\"%(etaotto*100)\n",
+    "print \"Mean effective pressure: %0.2f bar:\\n\"%(pm)\n",
+    "print \"Power developed: %0.2f kW\\n\"%(P)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.14 PAGE 106"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 4,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Air standard efficiency of the engine = 49.59 %\n",
+      "There is no change in efficiency when Helium is used as working fluid instead of air\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "t1=310#................#Min temperature in K\n",
+    "t3=1220#................#Max temperature in K\n",
+    "ga=1.4#................#Ratio of specific heats for air\n",
+    "cph=5.22#............#Specific heat at constant volume for helium in kJ/kg\n",
+    "cvh=3.13#...............#Specific heat at constant pressure for helium in kJ/kg\n",
+    "#Calculations \n",
+    "r=(t3/t1)**(1/((ga-1)*2))#..............#Compression ratio\n",
+    "etaotto=1-(1/(r**(ga-1)))#................#Air standard efficiency\n",
+    "gah=cph/cvh#................#Ratio of specific heats for Helium\n",
+    "rh=(t3/t1)**(1/((gah-1)*2))#..............#Compression ratio when Helium is used\n",
+    "etaottoh=1-(1/(rh**(gah-1)))#................#Air standard efficiency when Helium is used\n",
+    "print \"Air standard efficiency of the engine = %0.2f %%\"%(etaotto*100)\n",
+    "if ((round (etaotto)- round (etaottoh)) == 0):\n",
+    "    print \"There is no change in efficiency when Helium is used as working fluid instead of air\"\n"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.15 PAGE 108"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 5,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Power developed = 1.88 kW\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt\n",
+    "# Initialisation of Variables\n",
+    "t1=310#.........#Minimum temperature in K\n",
+    "t3=1450#............#maximum temperature in K\n",
+    "m=0.38#...........#Mass of working fluid in kg\n",
+    "cv=0.71#...........#Specific heat at constant volume in kJ/kg\n",
+    "#Calculations\n",
+    "t4=sqrt(t1*t3)#............#Temperature at the end of adiabatic expansion in K\n",
+    "t2=t4#\n",
+    "W=cv*(t3-t2-t4+t1)#..................#Work done in kJ/kg\n",
+    "P=W*(m/60)#.................#Power developed in kW\n",
+    "print \"Power developed = %0.2f kW\"%P"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.17 PAGE 113"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 6,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Efficiency of diesel engine = 61.19 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "r=15#...................#Compression ratio\n",
+    "ga=1.4#..............#Ratio os fpecific heats for air\n",
+    "perQ=6#................#Heat addition at constant pressure takes place at 6% of stroke\n",
+    "#Calculations\n",
+    "rho=1+((perQ/100)*(r-1))#.............#Cut off ratio\n",
+    "etad=1-((((rho**ga)-1)/(rho-1))*(1/(ga*(r**(ga-1)))))#..................#Efficiency of diesel engine\n",
+    "print \"Efficiency of diesel engine = %0.2f %%\"%(etad*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.18 PAGE 114"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 7,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Efficiency of diesel engine = 59.34 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt,pi\n",
+    "# Initialisation of Variables\n",
+    "L=0.25#...............#Engine stroke in m\n",
+    "D=0.15#..................#Engine bore in m\n",
+    "v2=0.0004#...............#Clearance volume in m**3\n",
+    "pers=5#...............#Percentage of stroke when fuel injection occurs\n",
+    "ga=1.4#..............#Ratio of specific heats\n",
+    "#Calculations\n",
+    "Vs=(pi/4)*D*D*L#..............#Swept volume in m**3\n",
+    "Vt=Vs+v2#....................#Total cylinder volume in m**3\n",
+    "v3=v2+((pers/100)*Vs)#..............#Volume at point of cut off\n",
+    "rho=v3/v2#............#Cut off ratio\n",
+    "r=1+(Vs/v2)#.............#Compression ratio\n",
+    "etad=1-((((rho**ga)-1)/(rho-1))*(1/(ga*(r**(ga-1)))))#..................#Efficiency of diesel engine\n",
+    "print \"Efficiency of diesel engine = %0.2f %%\"%(etad*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.19 PAGE 114"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 8,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Percentage loss in efficiency due to delay in cut off : 2.10\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "r=14#....................#Compression ratio\n",
+    "pers1=5#...............#Percentage of stroke when fuel cut off occurs\n",
+    "pers2=8#...............#Percentage of stroke when delayed fuel cut off occurs\n",
+    "v2=1#.....................#Clearance volume in m**3\n",
+    "ga=1.4#..................#Ratio of specific heats\n",
+    "#Calculations\n",
+    "#When the fuel is cut off at 5 %\n",
+    "rho1=((pers1/100)*(r-1))+1#.............#Cut off ratio\n",
+    "etad1=1-((((rho1**ga)-1)/(rho1-1))*(1/(ga*(r**(ga-1)))))#..................#Efficiency of diesel engine\n",
+    "#When the fuel is cut off at 8 %\n",
+    "rho2=((pers2/100)*(r-1))+1#.............# Delayed Cut off ratio\n",
+    "etad2=1-((((rho2**ga)-1)/(rho2-1))*(1/(ga*(r**(ga-1)))))#..................#Efficiency of diesel engine when cut off ratio is deyaled\n",
+    "print \"Percentage loss in efficiency due to delay in cut off : %0.2f\"%((etad1-etad2)*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.20 PAGE 115"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 9,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Cut off Percentage : 11.17\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from scipy.optimize import fsolve\n",
+    "# Initialisation of Variables\n",
+    "pm=7.5#.................#Mean effective pressure in bar\n",
+    "r=12.5#..................#Compression ratio\n",
+    "p1=1#....................#Initial pressure in bar\n",
+    "ga=1.4#.................#Ratio of specific heats\n",
+    "#Calculations\n",
+    "k=(pm*(ga-1)*(r-1))/(p1*(r**ga))#\n",
+    "c1=(r**(1-ga))/k#\n",
+    "c2=(-ga)/k#\n",
+    "c=1+(ga/k)-((r**(1-ga))/k)#\n",
+    "def F(rho):\n",
+    "    f=c1*(rho**ga)+c2*rho+c#\n",
+    "    return f\n",
+    "#Initial guess\n",
+    "rho=2#\n",
+    "#Derivative\n",
+    "def D(rho):\n",
+    "    z=c1*ga*(rho**(ga-1))+c2#\n",
+    "    return z\n",
+    "y=fsolve(F,rho)\n",
+    "perc=((y-1)/(r-1))*100#..................#Percentage of cutoff\n",
+    "print \"Cut off Percentage : %0.2f\"%perc"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.21 PAGE 115"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 1,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Temperature after adiabatic compression: 886.253082 K\n",
+      "\n",
+      "Pressure after adiabatic compression: 44.312654 bar\n",
+      "\n",
+      "Volume after adiabatic compression: 0.000673 m**3\n",
+      "\n",
+      "Temperature after isobaric compression: 1878.856533 K\n",
+      "\n",
+      "Pressure after isobaric compression: 44.312654 bar\n",
+      "\n",
+      "Volume after isobaric compression: 0.001427 m**3\n",
+      "\n",
+      "Temperature after adiabatic expansion: 858.996630 K\n",
+      "\n",
+      "Pressure after adiabatic expansion: 2.863322 bar\n",
+      "\n",
+      "Volume after adiabatic expansion: 0.010098 m**3\n",
+      "\n",
+      "Efficiency of diesel engine = 59.77 %\n",
+      "Mean effective pressure : 7.42\n",
+      "Power developed = 44.27 kW \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "D=0.2#.................#Engine bore in m\n",
+    "L=0.3#.............#Engine stroke in m\n",
+    "p1=1#................#Initial pressure in bar\n",
+    "N=380#.................#No of working cycles per min\n",
+    "t1=300#..............#Initial temperature in K\n",
+    "co=8#................#Cut off percentage\n",
+    "r=15#..................#Compression ratio\n",
+    "R=287#.................#gas constant in J/kg\n",
+    "ga=1.4#................#Ratio of specific heats\n",
+    "#Calculations\n",
+    "Vs=(pi/4)*D*D*L#.............#Stroke volume in m\n",
+    "v1=(r/(r-1))*Vs#................#Volume at the end of isochoric compression in m**3\n",
+    "m=(p1*v1*10**5)/(R*t1)#................#Mass of air in cylinder in kg/cycle\n",
+    "p2=p1*(r**ga)#.......................#Pressure at the end of isentropic compression in bar\n",
+    "t2=t1*(r**(ga-1))#....................#Temperature at the end of isentropic compression in K\n",
+    "v2=Vs/(r-1)#..................#Volume at the end of isentropic compressionin m**3\n",
+    "p3=p2#\n",
+    "rho=((r-1)*(co/100))+1#................#Cut off ratio\n",
+    "v3=rho*v2#.......................#Volume at the end of isobaric expansion in m**3\n",
+    "t3=t2*(v3/v2)#..................#Temperature at the end of isobaric expansion in K\n",
+    "p4=((rho/r)**ga)*p3#..............#Pressure at the end of adiabatic expansion in bar\n",
+    "t4=((rho/r)**(ga-1))*t3#..............#Temperature at the end of adiabatic expansion in K\n",
+    "v4=v1#\n",
+    "print \"Temperature after adiabatic compression: %f K\\n\"%(t2)\n",
+    "print \"Pressure after adiabatic compression: %f bar\\n\"%(p2)\n",
+    "print \"Volume after adiabatic compression: %f m**3\\n\"%(v2)\n",
+    "print \"Temperature after isobaric compression: %f K\\n\"%(t3)\n",
+    "print \"Pressure after isobaric compression: %f bar\\n\"%(p3)\n",
+    "print \"Volume after isobaric compression: %f m**3\\n\"%(v3)\n",
+    "print \"Temperature after adiabatic expansion: %f K\\n\"%(t4)\n",
+    "print \"Pressure after adiabatic expansion: %f bar\\n\"%(p4)\n",
+    "print \"Volume after adiabatic expansion: %f m**3\\n\"%(v4)\n",
+    "etad=1-((((rho**ga)-1)/(rho-1))*(1/(ga*(r**(ga-1)))))#..................#Efficiency of diesel engine\n",
+    "print \"Efficiency of diesel engine = %0.2f %%\"%(etad*100)\n",
+    "pm=p1*(r**ga)*(ga*(rho-1)-((r**(1-ga))*((rho**ga)-1)))*(1/(ga-1))*1/(r-1)#.......#Mean effective pressure \n",
+    "print \"Mean effective pressure : %0.2f\"%pm\n",
+    "Wdc=(pm*Vs*10**5)/1000#..................#Work done per cycle in kJ/cycle\n",
+    "P=(Wdc*N)/60#...........................#Power developed in kW\n",
+    "print \"Power developed = %0.2f kW \"%P"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.22 PAGE 118"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 2,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Mean effective pressure = 7.02 bar \n",
+      "Ratio of maximum pressure to mean effective pressure 6.49\n",
+      "Cycle efficiency = 60.48 %\n",
+      "Fuel consumption = 0.35 kg/kWh\n"
+     ]
+    }
+   ],
+   "source": [
+    "# Initialisation of Variables\n",
+    "rc=15.3#....................#Compression ratio\n",
+    "re=7.5#...................#Expansion ratio\n",
+    "cp=1.005#.................#Specific heat at constant pressure in kJ/kg K\n",
+    "cv=0.718#..................#Specific heat at constant volume in kJ/kgK\n",
+    "ga=1.4#....................#Ratio of specific heats\n",
+    "p1=1#....................#Initial pressure in bar\n",
+    "t1=300#..................#Initial temperature in K\n",
+    "etamech=0.8#..................#Mechanical efficiency\n",
+    "C=42000#...........................#Calorific value of fuel in kJ/kg\n",
+    "rita=0.5#.........................#Ratio of indicated thermal efficiency to air standard efficiency\n",
+    "R=287#..........................#Gas constant in kJ/kgK\n",
+    "#Calculations\n",
+    "t2=t1*(rc**(ga-1))#.................#Temperature at the end of adiabatic compression in K\n",
+    "p2=p1*(rc**ga)#...................#Pressure at the end of adiabatic compression in bar\n",
+    "t3=(rc*t2)/re#....................#Temperature at the end of constant pressure process in K\n",
+    "v2=1#..................#Volume at the end of adiabatic process in m**3\n",
+    "m=(p2*v2*10**5)/(R*t2)#..................#Mass of working fluid in kg\n",
+    "t4=t3*((1/re)**(ga-1))#...................#Temperature at the end of adiabatic expansion in K\n",
+    "W=(m*(cp*(t3-t2)))-(m*(cv*(t4-t1)))#........#Work done in kJ\n",
+    "pm=W/(rc-1)#..............................#Mean effective pressure in kN/m**2\n",
+    "print \"Mean effective pressure = %0.2f bar \"%(pm/100)\n",
+    "print \"Ratio of maximum pressure to mean effective pressure %0.2f\"%((p2*100)/(pm))\n",
+    "etacy=W/(m*cp*(t3-t2))#...............#Cycle efficiency\n",
+    "print \"Cycle efficiency = %0.2f %%\"%(etacy*100)\n",
+    "etaith=rita*etacy#..................#Indicated thermal efficiency\n",
+    "etabth=etaith*etamech#...............#Brake thermal efficiency\n",
+    "mf=3600/(etabth*C)#................#Fuel consumption per kWh\n",
+    "print \"Fuel consumption = %0.2f kg/kWh\"%mf"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.23 PAGE 123"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 3,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Efficiency of dual cycle : 63.76\n"
+     ]
+    }
+   ],
+   "source": [
+    "# Initialisation of Variables\n",
+    "Vs=0.0053#................#Swept volume in m**3\n",
+    "Vc=0.00035#...............#Clearance volume in m**3\n",
+    "v3=Vc#\n",
+    "v2=Vc#\n",
+    "p3=65#..................#Max pressure in bar\n",
+    "co=5#...................#Cut off percentage\n",
+    "p4=p3#ga=1.4#...............#Ratio of specific heats\n",
+    "t1=353#....................#Temperature at the start of compression in K\n",
+    "p1=0.9#...................#Pressure at the start of compression in bar\n",
+    "#Calculations\n",
+    "r=1+(Vs/Vc)#...................#Compression ratio\n",
+    "rho=(((co/100)*Vs)/Vc)+1#...................#Cut off ratio\n",
+    "p2=p1*(r**ga)#\n",
+    "Beta=p3/p2#.............................#Explosion ratio\n",
+    "etadual=1-((1/(r**(ga-1)))*((Beta*(rho**ga))-1)*(1/((Beta-1)+(Beta*ga*(rho-1)))))#............#Efficiency of dual cycle\n",
+    "print \"Efficiency of dual cycle : %0.2f\"%(etadual*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.24 PAGE 124"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 4,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Efficiency of dual cycle : 61.42\n"
+     ]
+    }
+   ],
+   "source": [
+    "# Initialisation of Variables\n",
+    "r=14#......................#Compression ratio\n",
+    "Beta=1.4#................#Explosion ratio\n",
+    "co=6#..................#Cut off percentage\n",
+    "ga=1.4#.................#Ratio of specific heats\n",
+    "#Calculation\n",
+    "rho=((co/100)*(r-1))+1#...............#Cut off ratio\n",
+    "etadual=1-((1/(r**(ga-1)))*((Beta*(rho**ga))-1)*(1/((Beta-1)+(Beta*ga*(rho-1)))))#............#Efficiency of dual cycle\n",
+    "print \"Efficiency of dual cycle : %0.2f\"%(etadual*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.25 PAGE 124"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 5,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Air standard efficiency = 57.55 %\n",
+      "Power developed = 51.39 kW\n"
+     ]
+    }
+   ],
+   "source": [
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "D=0.25#.................#Engine bore in m\n",
+    "L=0.3#.............#Engine stroke in m\n",
+    "p1=1#................#Initial pressure in bar\n",
+    "N=3#...............#No of cycles per second\n",
+    "p3=60#................#Maximum pressure in bar\n",
+    "t1=303#..............#Initial temperature in K\n",
+    "co=4#................#Cut off percentage\n",
+    "r=9#..................#Compression ratio\n",
+    "R=287#.................#gas constant in J/kg\n",
+    "cv=0.71#...............#Specific heat at constant volume in kJ/kgK\n",
+    "cp=1.0#.................#Specific heat at constant pressure in kJ/kgK\n",
+    "ga=1.4#...............#Ratio of specific heats\n",
+    "#Calculations\n",
+    "p4=p3#\n",
+    "Vs=(pi/4)*D*D*L#.............#Stroke volume in m**3\n",
+    "Vc=Vs/(r-1)#..................#Clearance volume in m**3\n",
+    "rho=((r-1)*(co/100))+1#................#Cut off ratio\n",
+    "v1=Vc+Vs#.................#Volume after isochoric compression in m**3\n",
+    "p2=p1*(r**ga)#................#Pressure after adiabatic compression in bar\n",
+    "t2=t1*(r**(ga-1))#..............#Temperature after adiabatic expansion in K\n",
+    "t3=(p3*t2)/p2#..............#Temperature after isochoric compression in K\n",
+    "t4=t3*rho#.....................#Temperature after isobaric expansion in K\n",
+    "t5=t4*((rho/r)**(ga-1))#.........#Temperature after adiabatic expansion in K\n",
+    "p5=p4*(rho/r)**ga#...............#Pressure after adiabatic expansion in bar\n",
+    "Qs=(cv*(t3-t2)+cp*(t4-t3))#.....#Heat supplied in kJ/kg\n",
+    "Qr=cv*(t5-t1)#...................#Heat rejected in kJ/kg\n",
+    "etast=1-(Qr/Qs)#.................#Air standard efficiency\n",
+    "print \"Air standard efficiency = %0.2f %%\"%(etast*100)\n",
+    "m=(p1*v1*10**5)/(R*t1)#...............#Mass of air in cycle\n",
+    "W=m*(Qs-Qr)#....................#Work done per cycle in kJ\n",
+    "P=W*N#............................#Power developed in kW\n",
+    "print \"Power developed = %0.2f kW\"%P"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.26 PAGE 127"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 1,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Temperature after adiabatic compression: 874.19 K\n",
+      "\n",
+      "Pressure after adiabatic compression: 21.67 bar\n",
+      "\n",
+      "Temperature after isochoric compression: 2742.67 K\n",
+      "\n",
+      "Pressure after isochoric compression: 68.00 bar\n",
+      "\n",
+      "Temperature after isobaric expansion: 3166.05 K\n",
+      "\n",
+      "Pressure after isobaric expansion: 68.00 bar\n",
+      "\n",
+      "Temperature after adiabatic expansion: 1392.38 K\n",
+      "\n",
+      "Pressure after adiabatic expansion: 3.84 bar\n",
+      "\n",
+      "Air standard efficiency = 58.24 %\n",
+      "Mean effective pressure = 11.09 bar\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "p1=1#................#Initial pressure in bar\n",
+    "t1=363#.............#Initial temperature in K\n",
+    "r=9#.................#Compression ratio\n",
+    "p3=68#...............#Max pressure\n",
+    "p4=p3#\n",
+    "Qs=1750#..............#Total heat supplied\n",
+    "ga=1.4#...............#Ratio of specific heats\n",
+    "R=287#................#Gas constant in kJ/kgK\n",
+    "cv=0.71#..............#Specific heat at constant volume in kJ/kgK\n",
+    "cp=1#................#Specific heat at constant pressure in kJ/kgK\n",
+    "#Calculations\n",
+    "p2=p1*((r)**ga)#............#Pressure at the end of adiabatic compression in bar\n",
+    "t2=t1*((r)**(ga-1))#..........#Temperature at the end of adiabatic compression in K\n",
+    "t3=t2*(p3/p2)#............#Temperature at the end of isochoric compression in K\n",
+    "Qv=cv*(t3-t2)#.............#Heat added at constant volume in kJ/kg\n",
+    "Qp=Qs-Qv#.....................#Heat added at constant pressure in kJ/kg\n",
+    "t4=(Qp/cp)+t3#................#Temperature at the end of isobaric expansion in kJ/kg\n",
+    "rho=t4/t3#.....................#Cut off ratio\n",
+    "p5=p4*((rho/r)**ga)#................#Pressure at the end of adiabatic expansion in kJ/kg\n",
+    "t5=t4*((rho/r)**(ga-1))#...........#Temperature at the end of adiabatic expansion in kJ/kg\n",
+    "print \"Temperature after adiabatic compression: %0.2f K\\n\"%(t2)\n",
+    "print \"Pressure after adiabatic compression: %0.2f bar\\n\"%(p2)\n",
+    "print \"Temperature after isochoric compression: %0.2f K\\n\"%(t3)\n",
+    "print \"Pressure after isochoric compression: %0.2f bar\\n\"%(p3)\n",
+    "print \"Temperature after isobaric expansion: %0.2f K\\n\"%(t4)\n",
+    "print \"Pressure after isobaric expansion: %0.2f bar\\n\"%(p4)\n",
+    "print \"Temperature after adiabatic expansion: %0.2f K\\n\"%(t5)\n",
+    "print \"Pressure after adiabatic expansion: %0.2f bar\\n\"%(p5)\n",
+    "Qr=cv*(t5-t1)#....................#Heat rejected in kJ\n",
+    "etast=1-(Qr/Qs)#.................#Air standard efficiency\n",
+    "print \"Air standard efficiency = %0.2f %%\"%(etast*100)\n",
+    "pm=(1/(r-1))*((68*(rho-1))+(((p4*rho)-(p5*r))/(ga-1))-((p2-r)/(ga-1)))#................#Mean effective pressure in bar\n",
+    "print \"Mean effective pressure = %0.2f bar\"%pm"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.27 PAGE 129"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 2,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Air standard efficiency = 65.30 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "t1=300#...............#Initial temperature\n",
+    "rmami=70#....................#Ratio of max pressure and min pressure\n",
+    "r=15#....................#Compression ratio\n",
+    "ga=1.4#.................#Ratio of specific heats\n",
+    "R=287#....................#Gas constant in kJ/kgK\n",
+    "t2=t1*(r**(ga-1))#.................#Temperature at the end of adiabatic compression in K\n",
+    "t3=t2*(rmami/(r**ga))#............#Temperature at the end of isochoric compression in K\n",
+    "t4=t3+((t3-t2)/ga)#..............#Temperature at the end of isobaric process in K\n",
+    "t5=t4/((1/(t4/(t3*r)))**(ga-1))#..........#Temperature at the end of adiabatic expansion in K\n",
+    "etast=1-((t5-t1)/((t3-t2)+ga*(t4-t3)))#..............#Air standard efficiency\n",
+    "print \"Air standard efficiency = %0.2f %%\"%(etast*100,)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.28 PAGE 131"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 3,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Thermal efficiency = 61.80 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "t1=373#.............#Initial temperature in K\n",
+    "p1=1#...............#Initial pressure in bar\n",
+    "p3=65#..............#Maximum pressure in bar\n",
+    "R=287#.................#Gas constant in kJ/kg\n",
+    "p4=p3#\n",
+    "ga=1.41#.................#Ratio of specific heats\n",
+    "Vs=0.0085#............#Swept volume in m**3\n",
+    "afr=21#...............#Air fuel ratio\n",
+    "r=15#.................#Compression ratio\n",
+    "C=43890#..............#Calorific value of fuel in kJ/kg\n",
+    "cp=1#................#Specific heat at constant pressure in kJ/kgK\n",
+    "cv=0.71#..............#Specific heat at constant volume in kJ/kgK\n",
+    "#Calculations\n",
+    "Vc=Vs/(r-1)#...............#Clearance volume in m**3\n",
+    "v2=Vc\n",
+    "v1=Vs+v2#\n",
+    "v3=Vc\n",
+    "v5=v1#\n",
+    "p2=p1*(r**ga)#.....................#Pressure at the end of adiabatic compression in bar\n",
+    "t2=t1*(r**(ga-1))#................#Temperature at the end of adiabatic compression in K\n",
+    "t3=(t2*p3)/p2#...................#Temperature at the end of isochoric compression in K\n",
+    "m=(p1*v1*10**5)/(R*t1)#............#Mass of air in the cycle in kg\n",
+    "Qv=m*cv*(t3-t2)#.....................#Heat added during constant volume process in kJ\n",
+    "fv=Qv/C#.............................#Fuel added during constant volume process in kg\n",
+    "mf=m/afr#..................#Total amount of fuel added in kg\n",
+    "mfib=mf-fv#....................#Total amount of fuel added in isobaric process in kg\n",
+    "Qib=mfib*C#....................#Total amount of heat added in isobaric process in kJ\n",
+    "t4=(Qib/((m+mf)*cp))+t3#........#Temperature at the end of isobaric process in K\n",
+    "v4=(v3*t4)/t3#..................#Volume at the end of isobaric process in m**3\n",
+    "t5=t4/((v5/v4)**(ga-1))#.........#Temperature at the end of isochoric expansion in K\n",
+    "Qrv=(m+mf)*cv*(t5-t1)#...............#Heat rejected during constant volume process in kJ\n",
+    "W=(Qib+Qv)-Qrv#................#Work done in kJ\n",
+    "etath=W/(Qib+Qv)#..................#Thermal efficiency\n",
+    "print \"Thermal efficiency = %0.2f %%\"%(etath*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.29 PAGE 133"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 4,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Temperature after adiabatic compression: 524.81 K\n",
+      "\n",
+      "Pressure after adiabatic compression: 15.59 bar\n",
+      "\n",
+      "Temperature after isochoric compression: 1201.99 K\n",
+      "\n",
+      "Pressure after isochoric compression: 35.70 bar\n",
+      "\n",
+      "Temperature after isobaric expansion: 3283.19 K\n",
+      "\n",
+      "Pressure after isobaric expansion: 35.70 bar\n",
+      "\n",
+      "Temperature after adiabatic expansion: 2195.60 K\n",
+      "\n",
+      "Pressure after adiabatic expansion: 4.78 bar\n",
+      "\n",
+      "Mean effective pressure = 10.92 bar\n",
+      "Engine efficiency = 32.95 %\n",
+      "Power of the engine = 171.53 kW\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "D=0.25#.............#Engine bore in m\n",
+    "L=0.4#..............#Engine stroke in m\n",
+    "t1=303#.............#Initial temperature in K\n",
+    "R=287#...............#Gas constant in kJ/kgK\n",
+    "p1=1#...............#Initial pressure in bar\n",
+    "N=8#................#No of working cycles per sec\n",
+    "cv=0.71#.............#Specific heat at constant volume in kJ/kgK\n",
+    "cp=1#.................#Specific heat at constant pressure in kJ/kgK\n",
+    "n=1.25#.............#Adiabatic index\n",
+    "rc=9#...............#Compression ratio\n",
+    "re=5#...............#Expansion ratio\n",
+    "rqptqe=2#...........#Ratio of heat liberated at constant pressure to heat liberated at constant volume\n",
+    "#Calculations\n",
+    "p2=p1*(rc**n)#.......................#Pressure at the end of adiabatic compression in bar\n",
+    "t2=t1*(rc**(n-1))#...................#Temperature at the end of adiabatic compression in K\n",
+    "rho=rc/re#..........................#Cut off ratio\n",
+    "t3=(2*cv*t2)/((2*cv)-(cp*(rho-1)))#...............#Temperature at the end of isochoric compression in K\n",
+    "p3=p2*(t3/t2)#....................................#Pressure at the end of isochoric compression in bar\n",
+    "p4=p3#t4=rho*t3#.................................#Temperature and pressure at the end of isobaric process\n",
+    "p5=p4*(1/(re**n))#.................................#Pressure at the end of adiabatic expansion in bar\n",
+    "t5=t4*(1/(re**(n-1)))#.............................#Temperature at the end of adiabatic expansion in K\n",
+    "pm=(1/(rc-1))*((p3*(rho-1))+(((p4*rho)-(p5*rc))/(n-1))-((p2-(p1*rc))/(n-1)))#...............#Mean effective pressure \n",
+    "print \"Temperature after adiabatic compression: %0.2f K\\n\"%(t2)\n",
+    "print \"Pressure after adiabatic compression: %0.2f bar\\n\"%(p2)\n",
+    "print \"Temperature after isochoric compression: %0.2f K\\n\"%(t3)\n",
+    "print \"Pressure after isochoric compression: %0.2f bar\\n\"%(p3)\n",
+    "print \"Temperature after isobaric expansion: %0.2f K\\n\"%(t4)\n",
+    "print \"Pressure after isobaric expansion: %0.2f bar\\n\"%(p4)\n",
+    "print \"Temperature after adiabatic expansion: %0.2f K\\n\"%(t5)\n",
+    "print \"Pressure after adiabatic expansion: %0.2f bar\\n\"%(p5)\n",
+    "print \"Mean effective pressure = %0.2f bar\"%pm\n",
+    "Vs=(pi/4)*D*D*L#....................#Swept volume in m**3\n",
+    "W=(pm*(10**5)*Vs)/1000#.................#Work done per cycle in kJ\n",
+    "m=(p1*(10**5)*(rc/(rc-1))*Vs)/(R*t1)#.....................#Mass of air per cycle in kg\n",
+    "Qs=m*(cv*(t3-t2)+cp*(t4-t3))#.....................#Heat supplied per cycle in kJ\n",
+    "eta=W/Qs#....................#Engine efficiency\n",
+    "print \"Engine efficiency = %0.2f %%\"%(eta*100)\n",
+    "P=W*N#.................#Power of the engine in kW\n",
+    "print \"Power of the engine = %0.2f kW\"%P"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.31 PAGE 140"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 5,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Work done = 282.90 kJ/kg\n",
+      "Efficiency of cycle = 32.64 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "cp=0.92#..................#Specific heat at constant pressure in kJ/kgK\n",
+    "cv=0.75#..................#Specific heat at constant volume in kJ/kgK\n",
+    "p1=1#...................#Pressure at the end of adiabatic expansion in bar\n",
+    "p2=p1#...................#Pressure at the end of isobaric compression in bar\n",
+    "p3=4#....................#Pressure at the end of isobaric compression in bar\n",
+    "p4=16#...................#Final pressure after heat addition in bar\n",
+    "t2=300#.....................#Temperature at the end of isobaric compression in K\n",
+    "ga=1.22#................#Ratio of specific heats\n",
+    "#Calculations\n",
+    "t3=t2*((p3/p2)**((ga-1)/ga))#............#Temperature at the end of isobaric compression in K\n",
+    "t4=(p4*t3)/p3#........................#Final temperature after heat addition in K\n",
+    "t1=t4/((p4/p1)**((ga-1)/ga))#...................#Temperature at the end of adiabatic compression in K\n",
+    "Qs=cv*(t4-t3)#.........................#Heat supplied in kJ/kg\n",
+    "Qr=cp*(t1-t2)#.........................#Heat rejected in kJ/kg\n",
+    "W=Qs-Qr#.......................#Work done per kg of gas in kJ\n",
+    "print \"Work done = %0.2f kJ/kg\"%W\n",
+    "eta=W/Qs#......................#Efficiency of cycle\n",
+    "print \"Efficiency of cycle = %0.2f %%\"%(eta*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.32 PAGE 145"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 6,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Cycle efficiency = 40.07 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "p1=101.325#....................#Pressure of intake air in kPa\n",
+    "t1=300#.......................#Temperature of intake air in kPa\n",
+    "rp=6#.........................#Pressure ratio in the cycle\n",
+    "ga=1.4#.........................#Ratio of specific heats\n",
+    "rtc=2.5#...........................#Ratio of turbine work and compressor work\n",
+    "#Calculations\n",
+    "t2=t1*(rp**((ga-1)/ga))#..................#Temperature at the end of isentropic expansion in K\n",
+    "t3=(rtc*(t2-t1))/(1-(1/(rp**((ga-1)/ga))))#........#Temperature at the end of isobaric expansion in K\n",
+    "t4=t3/(rp**((ga-1)/ga))#.......................#Temperature at the end of isentropic compression in K\n",
+    "eta=(t3-t4-t2+t1)/(t3-t2)#...................#Cycle efficiency\n",
+    "print \"Cycle efficiency = %0.2f %%\"%(eta*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.33 PAGE 147"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 7,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Power developed per kg of gas per second = 362.01 kW \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "p1=1#....................#Intake pressure in bar\n",
+    "p2=5#....................#Supply pressure in bar\n",
+    "t3=1000#..................#Supply temperature in Kelvin\n",
+    "cp=1.0425#................#Specific heat at constant pressure in kJ/kgK\n",
+    "cv=0.7662#.................#Specific heat at constant volume in kJ/kgK\n",
+    "ga=cp/cv#..................#Ratio of specific heats\n",
+    "#Calculations\n",
+    "t4=t3*((p1/p2)**((ga-1)/ga))#\n",
+    "P=cp*(t3-t4)#.....................#Power developed per kg of gas per second in kW\n",
+    "print \"Power developed per kg of gas per second = %0.2f kW \"%P"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.34 PAGE 147"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 8,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Temperature at turbine inlet = 423.51 K\n",
+      "Power developed = 13.85 kW\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "ma=0.1#...................#Air supplied in kg/s\n",
+    "p1=1#.....................#Supply pressure in bar\n",
+    "t4=285#.................#Temperature of air when supplied to cabin in K\n",
+    "p2=4#...................#Pressure at inlet to turbine in bar\n",
+    "cp=1.0#..................#Specific heat at constant pressure in kJ/kgK\n",
+    "ga=1.4#..................#Ratio of specific heats\n",
+    "#Calculations\n",
+    "t3=t4*((p2/p1)**((ga-1)/ga))#................#Temperature at turbine inlet in K\n",
+    "print \"Temperature at turbine inlet = %0.2f K\"%t3\n",
+    "P=ma*cp*(t3-t4)#...........................#Power developed in kW\n",
+    "print \"Power developed = %0.2f kW\"%P"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.35 PAGE 148"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 9,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Efficiency of the cycle : 30.09\n",
+      "Heat supplied to the air = 456.17 kJ/kg \n",
+      "Work available at the shaft = 137.25 kJ/kg \n",
+      "Heat rejected in the cooler = 318.92 kJ/kg \n",
+      "Temperature of air leaving the turbine = 610.33 K \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "p1=1#......................#Pressure of air entering the compressor in bar\n",
+    "p2=3.5#.................#Pressure of air while leaving the compressor in bar\n",
+    "t1=293#..................#Temperature of air at the onlet of the compressor in K\n",
+    "t3=873#.................#Temperature of air at the turbine inlet in K\n",
+    "cp=1.005#...............#Specific heat at constant pressure in kJ/kgK\n",
+    "ga=1.4#...................#Ratio of specific heats\n",
+    "#Calculations\n",
+    "rp=p2/p1#....................#Pressure ratio of the cycle\n",
+    "eta=1-(1/(rp**((ga-1)/ga)))#..............#Efficiency of the cycle\n",
+    "print \"Efficiency of the cycle : %0.2f\"%(eta*100)\n",
+    "t2=t1*((rp**((ga-1)/ga)))#................#Temperature of air while leaving the compressor in K\n",
+    "q1=cp*(t3-t2)#................#Heat supplied to the air in kJ/kg\n",
+    "print \"Heat supplied to the air = %0.2f kJ/kg \"%(q1)\n",
+    "W=eta*q1#........................#Work available at the shaft in kJ/kg\n",
+    "print \"Work available at the shaft = %0.2f kJ/kg \"%W\n",
+    "q2=q1-W#................#Heat rejected in the cooler in kJ/kg\n",
+    "print \"Heat rejected in the cooler = %0.2f kJ/kg \"%q2\n",
+    "t4=t3/(rp**((ga-1)/ga))#.......................#Temperature of air leaving the turbine in K\n",
+    "print \"Temperature of air leaving the turbine = %0.2f K \"%t4"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.36 PAGE 149"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 10,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Maximum temperature = 1251.38 K \n",
+      "Cycle efficiency = 40.07 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "p1=1#...................#Pressure of air entering the compressor in bar\n",
+    "t1=300#.................#Temperature of air entering the compressor in bar\n",
+    "rp=6#...................#Pressure ratio\n",
+    "rtc=2.5#.................#Ratio of turbine work to compressor work\n",
+    "ga=1.4#............#Ratio of specific heats\n",
+    "#calculations\n",
+    "t2=t1*(rp**((ga-1)/ga))#..................#Temperature at the end of isentropic expansion in K\n",
+    "t3=(rtc*(t2-t1))/(1-(1/(rp**((ga-1)/ga))))#........#Temperature at the end of isobaric expansion in K\n",
+    "t4=t3/(rp**((ga-1)/ga))#.......................#Temperature at the end of isentropic compression in K\n",
+    "eta=(t3-t4-t2+t1)/(t3-t2)#...................#Cycle efficiency\n",
+    "print \"Maximum temperature = %0.2f K \"%t3\n",
+    "print \"Cycle efficiency = %0.2f %%\"%(eta*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.37 PAGE 150"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 11,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Rate of fuel consumption = 0.02 kg/s \n",
+      "Mass flow rate of air = 1.68 kg/s \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt\n",
+    "# Initialisation of Variables\n",
+    "t1=303#........................#Min temperature in K\n",
+    "t3=1073#........................#Max temperature in K\n",
+    "C=45000#.....................#Calorific value of fuel in kJ/kg\n",
+    "cp=1#....................#Specific heat at constant pressure in kJ/kgK\n",
+    "ga=1.4#........................#Ratio os specific heats\n",
+    "diftc=100#..................#Difference between work done by turbine and compressor in kW\n",
+    "#Calculations\n",
+    "t2=sqrt(t1*t3)# t4 = t2#.....#Assumed\n",
+    "mf=diftc/(C*(1-((t4-t1)/(t3-t2))))#................#Fuel used in kg per second\n",
+    "print \"Rate of fuel consumption = %0.2f kg/s \"%mf\n",
+    "ma=(diftc-(mf*(t3-t4)))/((t3-t4-cp*(t2-t1)))#............#Rate of air consumption in kg/s\n",
+    "print \"Mass flow rate of air = %0.2f kg/s \"%(ma)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.38 PAGE 151"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 12,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Compressor work = 259.32 kJ/kg \n",
+      "Turbine work = 351.64 kJ/kg \n",
+      "Heat supplied = 517.54 kJ/kg \n",
+      "Cycle efficiency = 17.84 %\n",
+      "Actual exhaust temperature of turbine = 723.11 K\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "t1=300#.................#Inlet temperature in K\n",
+    "p1=1#....................#Inlet pressure in bar\n",
+    "ma=1#....................#Mass of air in kg\n",
+    "rp=6.25#.............#Pressure ratio\n",
+    "t3=1073#.....#Maximum temperature in K\n",
+    "etac=0.8#............#Efficiency of compressor\n",
+    "etat=0.8#.............#Efficiency of turbine\n",
+    "ga=1.4#.................#Ratio of specific heats\n",
+    "cp=1.005#.............#Specific heat at constant pressure in kJ/kgK\n",
+    "#Calculations\n",
+    "t2=t1*(rp**((ga-1)/ga))#...........#Ideal Temperature of air while leaviing the compressor in K\n",
+    "t21=((t2-t1)/etac)+t1#............#Actual Temperature of air while leaviing the compressor in K\n",
+    "Wcomp=ma*cp*(t21-t1)#.............#Compressor work in kJ/kg\n",
+    "t4=t3/(rp**((ga-1)/ga))#........#Ideal temperature of air while leaving the turbine in K\n",
+    "t41=t3-(etat*(t3-t4))#..........#Actual temperature of air while leaving the turbine in K\n",
+    "Wtur=ma*cp*(t3-t41)#..............#Turbine work in kJ/kg\n",
+    "Wnet=Wtur-Wcomp#.................#Net work produced in kJ/kg\n",
+    "Qs=ma*cp*(t3-t21)#.................#Heat supplied in kJ/kg\n",
+    "print \"Compressor work = %0.2f kJ/kg \"%(Wcomp)\n",
+    "print \"Turbine work = %0.2f kJ/kg \"%Wtur\n",
+    "print \"Heat supplied = %0.2f kJ/kg \"%Qs\n",
+    "print \"Cycle efficiency = %0.2f %%\"%((Wnet/Qs)*100)\n",
+    "print \"Actual exhaust temperature of turbine = %0.2f K\"%t41"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.39 PAGE 153"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 13,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Air fuel ratio is 56:1\n"
+     ]
+    }
+   ],
+   "source": [
+    "# Initialisation of Variables\n",
+    "etat=0.85#..............#Turbine efficiency\n",
+    "etac=0.8#...............#Compressor efficiency\n",
+    "t3=1148#................#Max temperature in K\n",
+    "t1=300#................#Temperature of working fluid when entering the compressor in Kelvin\n",
+    "cp=1#...................#specific heat at constant pressure in kJ/kgK\n",
+    "ga=1.4#................#ratio of specific heats\n",
+    "p1=1#...................#Pressure of working fluid while entering the compressor in bar\n",
+    "rp=4#...................#Pressure ratio\n",
+    "C=42000#...............#Calorific value of fuel used in kJ/kgK\n",
+    "perlcc=10#.............#Percentage loss of calorific value in combustion chamber\n",
+    "\n",
+    "#calculations\n",
+    "p2=p1*rp#.................#pressure of air while leaving the compressor in bar\n",
+    "etacc=1-(perlcc/100)#............#efficiency of combustion chamber\n",
+    "t2=t1*(rp**((ga-1)/ga))#...........#Ideal Temperature of air while leaviing the compressor in K\n",
+    "t21=((t2-t1)/etac)+t1#............#Actual Temperature of air while leaviing the compressor in K\n",
+    "afr=((C*etacc)/(cp*(t3-t21)))-1#...........#Air fuel ratio\n",
+    "print \"Air fuel ratio is %d:1\"%round(afr)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 3.40 PAGE 154"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 14,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Work done in process 1-2 = 148.93 kJ/kg \n",
+      "Heat rejected in process 1-2 = 148.93 kJ/kg \n",
+      "Work done in process 2-3 = 0.00 kJ/kg \n",
+      "Heat rejected in process 2-3 = 0.00 kJ/kg \n",
+      "Work done in process 3-4 = 446.80 kJ/kg \n",
+      "Heat rejected in process 3-4 = 446.80 kJ/kg\n",
+      "Work done in process 4-1 = 297.87 kJ/kg \n",
+      "Heat rejected in process 4-1 = 297.87 kJ/kg \n",
+      "Thermal efficiency of the cycle = 66.67 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from math import log\n",
+    "# Initialisation of Variables\n",
+    "p1=1#...........#pressure before isothermal compression in bar\n",
+    "t1=310#.........#temperature before isothermal compression in K\n",
+    "p3=16#.........#pressure before isothermal expansion in bar\n",
+    "t3=930#.........#temperature before isothermal expansion in K\n",
+    "R=287#.............#Gas constant in kJ/kgK\n",
+    "#Calculations\n",
+    "v1=(R*t1)/(p1*10**5)#...............#Volume before isothermal compression in m**3\n",
+    "v3=(R*t3)/(p3*10**5)#...............#Volume before isothermal expansion in m**3\n",
+    "v2=v3#v4=v1#.................#2-3 and 1-4 are isochoric processes\n",
+    "r=v1/v2#...................#Compression ratio\n",
+    "q12=R*t1*log(r)#...............#Work done and heat rejected in process 1-2\n",
+    "w12=q12#\n",
+    "print \"Work done in process 1-2 = %0.2f kJ/kg \"%(q12/1000)\n",
+    "print \"Heat rejected in process 1-2 = %0.2f kJ/kg \"%(w12/1000)\n",
+    "q23=0#w23=q23#..................#COnstant volume process and hence work done is zero\n",
+    "print \"Work done in process 2-3 = %0.2f kJ/kg \"%(q23/1000)\n",
+    "print \"Heat rejected in process 2-3 = %0.2f kJ/kg \"%(q23/1000)\n",
+    "q34=R*t3*log(r)#...............#Work done and heat rejected in process 1-2\n",
+    "w34=q34#\n",
+    "print \"Work done in process 3-4 = %0.2f kJ/kg \"%(q34/1000)\n",
+    "print \"Heat rejected in process 3-4 = %0.2f kJ/kg\"%(w34/1000)\n",
+    "q41=q34-q12\n",
+    "w41=q41#\n",
+    "print \"Work done in process 4-1 = %0.2f kJ/kg \"%(q41/1000)\n",
+    "print \"Heat rejected in process 4-1 = %0.2f kJ/kg \"%(w41/1000)\n",
+    "etath=w41/q34#.....................#Thermal efficiency\n",
+    "print \"Thermal efficiency of the cycle = %0.2f %%\"%(etath*100)"
+   ]
+  }
+ ],
+ "metadata": {
+  "kernelspec": {
+   "display_name": "Python 2",
+   "language": "python",
+   "name": "python2"
+  },
+  "language_info": {
+   "codemirror_mode": {
+    "name": "ipython",
+    "version": 2
+   },
+   "file_extension": ".py",
+   "mimetype": "text/x-python",
+   "name": "python",
+   "nbconvert_exporter": "python",
+   "pygments_lexer": "ipython2",
+   "version": "2.7.9"
+  }
+ },
+ "nbformat": 4,
+ "nbformat_minor": 0
+}
diff --git a/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER4_2.ipynb b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER4_2.ipynb
new file mode 100644
index 00000000..82c4af35
--- /dev/null
+++ b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER4_2.ipynb
@@ -0,0 +1,448 @@
+{
+ "cells": [
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "# CHAPTER 4 - Fuel-Air & Actual Cycles"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 4.2 PAGE 187"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 1,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The percentage change in the efficiency of otto cycle = -0.71 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from math import log\n",
+    "# Initialisation of Variables\n",
+    "r=8#..........................#Compression Ratio\n",
+    "ga=1.4#.......................#Degree of freedom for the gas\n",
+    "Cvinc=1.1#....................#Increase of specific heat at constant volume in percentage\n",
+    "#Calculations\n",
+    "eta=1-1/(r**(ga-1))#...........#efficiency of otto cycle\n",
+    "deta=(1-eta)*(ga-1)*log(r)*(Cvinc/100)#............#Change in efficiency\n",
+    "etach=-deta/eta#............................#Percentage change in efficiency of change in efficiency\n",
+    "print \"The percentage change in the efficiency of otto cycle = %0.2f %%\"%(etach*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 4.3 PAGE 187"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 3,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The percentage change in the efficiency of otto cycle = -1.98 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from math import log\n",
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "r=7#..........................#Compression Ratio\n",
+    "ga=1.4#.......................#Degree of freedom for the gas\n",
+    "Cvinc=3#....................#Increase of specific heat at constant volume in percentage\n",
+    "#Calculations\n",
+    "eta=1-1/(r**(ga-1))#...........#efficiency of otto cycle\n",
+    "deta=(1-eta)*(ga-1)*log(r)*(Cvinc/100)#............#Change in efficiency\n",
+    "etach=-deta/eta#............................#Percentage change in efficiency of change in efficiency\n",
+    "print \"The percentage change in the efficiency of otto cycle = %0.2f %%\"%(etach*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 4.4 PAGE 188"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 4,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Percentage change = -1.15 efficiency\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import log\n",
+    "# Initialisation of Variables\n",
+    "r=18#..........................#Compression Ratio\n",
+    "co=5#..........................#Cut off percent of stroke\n",
+    "cv=0.71#.......................#Mean specific heat for cycle in kJ/kg K\n",
+    "R=0.285#.......................#Charecteristic gas constant in kJ/kh K\n",
+    "cvinc=2#.......................#Percentage increase in mean specific heat of the cycle\n",
+    "#Calculation\n",
+    "rho=(co/100)*(r-1)+1#\n",
+    "ga=1+(R/cv)#\n",
+    "eta=1-(1/(ga*(r**(ga-1))))*((rho**ga)-1)/(rho-1)#.....................#Efficiency of diesel cycle \n",
+    "etach=-((1-eta)/eta)*(ga-1)*(log(r)-(((rho**ga)*log(rho))/((rho**ga)-1))+(1/ga))*(cvinc/100)#...#Variation in the air standard efficiency\n",
+    "print \"Percentage change = %0.2f efficiency\"%(etach*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 4.5 PAGE 189"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 5,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Max pressure in the cylinder = 65.52 bar \n",
+      "Max pressure for constant specific heat = 93.52 bar \n"
+     ]
+    }
+   ],
+   "source": [
+    "from math import sqrt,log\n",
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "r=7#......................#Compression ratio\n",
+    "C=44000#..................#Calorific value of fuel used in kJ/kg\n",
+    "afr=15#...................#Air fuel ratio\n",
+    "t1=338#....................#Temperature of the charge at the end of the stroke in Kelvin\n",
+    "p1=1#......................#Pressure of the charge at the end of the stroke in bar\n",
+    "n=1.33#....................#Index of compression\n",
+    "cv=0.71#......#Specific heat constant at constant volume in kJ/kgK\n",
+    "k=20*10**(-5)#\n",
+    "#Calculations\n",
+    "p2=p1*(r)**n#\n",
+    "t2=(t1*p2)/(p1*r)#\n",
+    "ha=C/(afr+1)#......................#Heat added per kg of charge in kJ\n",
+    "t3=((-2*cv)+sqrt((4*cv*cv)+(4*k*((2*cv*t2)+(k*t2*t2)+(2*ha)))))/(2*k)#\n",
+    "p3=(p2*t3)/t2#.............................#Max pressure for constant volume process in bar\n",
+    "P3=p2*((ha/cv)+t2)/t2#.....................#Max pressure for constant specific heat in bar\n",
+    "print \"Max pressure in the cylinder = %0.2f bar \"%(p3)\n",
+    "print \"Max pressure for constant specific heat = %0.2f bar \"%P3"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 4.6 PAGE 190"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 2,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Max pressure in the cylinder = 102.27 bar \n",
+      "Max pressure for constant specific heat = 150.64 bar \n"
+     ]
+    }
+   ],
+   "source": [
+    "from math import sqrt,log\n",
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "r=10#......................#Compression ratio\n",
+    "C=48000#..................#Calorific value of fuel used in kJ/kg\n",
+    "afr=15#...................#Air fuel ratio\n",
+    "t1=330#....................#Temperature of the charge at the end of the stroke in Kelvin\n",
+    "p1=1#......................#Pressure of the charge at the end of the stroke in bar\n",
+    "n=1.36#....................#Index of compression\n",
+    "cv=0.7117#......#Specific heat constant at constant volume in kJ/kgK\n",
+    "k=2.1*10**(-4)#\n",
+    "#Calculations\n",
+    "p2=p1*(r)**n#\n",
+    "t2=t1*((p2/p1)**((n-1)/n))#\n",
+    "ha=C/(afr+1)#......................#Heat added per kg of charge in kJ\n",
+    "t3=((-2*cv)+sqrt((4*cv*cv)+(4*k*((2*cv*t2)+(k*t2*t2)+(2*ha)))))/(2*k)#\n",
+    "p3=(p2*t3)/t2#.............................#Max pressure for constant volume process in bar\n",
+    "P3=p2*((ha/cv)+t2)/t2#.....................#Max pressure for constant specific heat in bar\n",
+    "print \"Max pressure in the cylinder = %0.2f bar \"%p3\n",
+    "print \"Max pressure for constant specific heat = %0.2f bar \"%P3"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 4.7 PAGE 191"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 3,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Percentage of the stroke when the combustion is completed is  9.77\n"
+     ]
+    }
+   ],
+   "source": [
+    "from math import sqrt,log\n",
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "r=15#......................#Compression ratio\n",
+    "C=43000#..................#Calorific value of fuel used in kJ/kg\n",
+    "afr=27#...................#Air fuel ratio\n",
+    "t2=870#....................#Temperature of the charge at the end of the stroke in Kelvin\n",
+    "cv=0.71#......#Specific heat constant at constant volume in kJ/kgK\n",
+    "R=0.287#.........................#Gas constant in kJ/kgK\n",
+    "k=20*10**(-5)#\n",
+    "#Calculations\n",
+    "cp=cv+R#............................#Specific heat at constant pressure\n",
+    "ha=C/(afr+1)#......................#Heat added per kg of charge in kJ\n",
+    "t3=((-2*cp)+sqrt((4*cp*cp)+(4*k*((2*cp*t2)+(k*t2*t2)+(2*ha)))))/(2*k)#\n",
+    "co=((t3/t2)-1)/(r-1)#.............#combustion occupies this amt of stroke \n",
+    "print \"Percentage of the stroke when the combustion is completed is \",round(co*100,2)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 4.8 PAGE 192"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 4,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Max pressure in the cylinder = 73.23 bar \n",
+      "Percentage of the stroke when the combustion is completed is  2.42\n"
+     ]
+    }
+   ],
+   "source": [
+    "from math import sqrt,log\n",
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "r=14#......................#Compression ratio\n",
+    "t1=87+273#....................#Temperature of the charge at the end of the stroke in Kelvin\n",
+    "p1=1#......................#Pressure of the charge at the end of the stroke in bar\n",
+    "hsupa=1700#............................#heat supplied per kg of air in kJ\n",
+    "cv=0.71#......#Specific heat constant at constant volume in kJ/kgK\n",
+    "k=20*10**(-5)#\n",
+    "ga=1.4#.....................#Degree of freedom \n",
+    "R=0.287#......................#Gas constant in kJ/kgK\n",
+    "#Calculations\n",
+    "p2=p1*(r)**ga#\n",
+    "t2=t1*(r**(ga-1))#\n",
+    "ha=hsupa/2#......................#Heat added per kg of charge in kJ\n",
+    "t3=((-2*cv)+sqrt((4*cv*cv)+(4*k*((2*cv*t2)+(k*t2*t2)+(2*ha)))))/(2*k)#\n",
+    "p3=(p2*t3)/t2#.............................#Max pressure for constant volume process in bar\n",
+    "P3=p2*((ha/cv)+t2)/t2#.....................#Max pressure for constant specific heat in bar\n",
+    "print \"Max pressure in the cylinder = %0.2f bar \"%p3\n",
+    "cp=cv+R#.................................#Heat capacity at constant pressure in kJ/kgK\n",
+    "t4=((-2*cp)+sqrt((4*cp*cp)+(4*k*((2*cp*t3)+(k*t3*t3)+(2*ha)))))/(2*k)#\n",
+    "co=((t4/t3)-1)/(r-1)#.............#combustion occupies this amt of stroke \n",
+    "print \"Percentage of the stroke when the combustion is completed is \",round(co*100,2)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 4.9 PAGE 193"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 5,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Maximum temperature ignoring molecular expansion = 4862.39 Kelvin \n",
+      "Maximum pressure ignoring molecular expansion = 113.41 bar \n",
+      "Maximum temperature considering molecular expansion = 4862.39 Kelvin \n",
+      "Maximum pressure considering molecular expansion = 122.86 bar\n"
+     ]
+    }
+   ],
+   "source": [
+    "from math import sqrt,log\n",
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "r=8#...........................#Compression ratio\n",
+    "C=44000#............#Calorific value of fuel in kJ/kg\n",
+    "afr=13.8#.....................#Air fuel ratio\n",
+    "t1=343#.............................#Temperature of the mixture at the beginning of the compression in Kelvin\n",
+    "p1=1#........................#Pressure of the mixture at the beginning of the compression in bar\n",
+    "cv=0.716#.....................#Specific heat at constant volume in kJ/kgK\n",
+    "In=1.35#.......................#Index of compression\n",
+    "nc=6#..........................#No of carbon elements in the given fuel\n",
+    "nh=14#.........................#No of hydrogen elements in the given fuel\n",
+    "mc=12#...........................#Atomic mass of carbon in amu\n",
+    "mh=2#.............................#atomic mass of hydrogen molecule in amu\n",
+    "mo=32#...........................#Atomic mass of oxygen molecule in amu\n",
+    "#Calculations\n",
+    "#The chemical equation is C6H14 + xO2 ==> yCO2 + zH2O \n",
+    "#x is the no of oxygen molecules required for complete combustion\n",
+    "#y is the no of carbon dioxide molecules produced in complete combustion\n",
+    "#z is the no of Water molecules produced in complete combustion\n",
+    "y=nc#............................#As no of CO2 molecules is equal to no of C atoms in the fuel\n",
+    "z=nh/2#..........................#No of H2O molecules is equal to half the no of H atoms in the fuel\n",
+    "x=(z/2)+y#...........................#No of oxygen molecules required for combustionis half the no of water molecules plus the no of oxygen molecules \n",
+    "gafr=((x*32)*(100/23))/((mc*y)+(mh*z))#.................#Gravimetric air fuel ratio\n",
+    "ms=(gafr/afr)*100#......................#Actual mixture strength\n",
+    "#Since the mixture strength is greater than 100 %\n",
+    "#The mixture is rich in fuel. The combustion is therefore incompplete and hence CO will be formed\n",
+    "d=ms/100#......................#No of fuel molecules required for combustion\n",
+    "#The chemical equation is d(C6H14) + 9.5(O2) ==> a(CO2) + b(CO) + c(H2O) \n",
+    "c=(d*nh)/2#...............................#No of H2O molecules is equal to half the no of H atoms in the fuel\n",
+    "a=(x*2)-(d*nc)-c#........................#Equating atoms of the same element on both sides of equation\n",
+    "b=(d*nc)-a#\n",
+    "#By adding nitrogen on both sides, we are adding the same molecular weight on both sides.\n",
+    "#Air is 79 % nitrogen and 21 % oxygen\n",
+    "#Both N2 and O2 are diatomic molecules\n",
+    "n=x*(79/21)#.............................#No of nitrogen molecules \n",
+    "mbc=d+x+n#.............................#Moles before combustion\n",
+    "mac=a+b+c+n#.............................#Moles after expansion\n",
+    "me=(mac-mbc)/mbc#........................#Molecular expansion\n",
+    "t2=(t1*(r**(In-1)))#\n",
+    "t3=(t2+(C/((afr+1)*cv)))#..................#Maximum temperature ignoring molecular expansion in Kelvin\n",
+    "p3=p1*r*(t3/t1)#...........................#Maximum pressure ignoring molecular expansion in bar\n",
+    "t3me=t3#...............................#Maximum temperature considering molecular expansion in Kelvin\n",
+    "p3me=p3*(mac/mbc)#....................#Maximum pressure considering molecular expansion in bar\n",
+    "print \"Maximum temperature ignoring molecular expansion = %0.2f Kelvin \"%t3\n",
+    "print \"Maximum pressure ignoring molecular expansion = %0.2f bar \"%p3\n",
+    "print \"Maximum temperature considering molecular expansion = %0.2f Kelvin \"%t3me\n",
+    "print \"Maximum pressure considering molecular expansion = %0.2f bar\"%p3me"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 4.10 PAGE 194"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 6,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The cycle work = 872.05 kJ/kg \n",
+      "The cycle efficiency = 44.99 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from math import sqrt,log\n",
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "r=7#....................#Compression Ratio\n",
+    "t2=715#.................#Temperature at the end of isentropic compression in Kelvin\n",
+    "t4=1610#................#Temperature at the end of expansion in Kelvin\n",
+    "#Calculations\n",
+    "vr2=65.8#..................#From steam table\n",
+    "u2=524.2#..................#From steam table\n",
+    "vr4=5.69#..................#From steam table\n",
+    "u4=1307.63#..................#From steam table\n",
+    "vr1=r*vr2#\n",
+    "t1=338#..................#From steam table\n",
+    "u1=241.38#..................#From steam table\n",
+    "vr3=vr4/r#\n",
+    "t3=2800#..................#From steam table\n",
+    "u3=2462.5#..................#From steam table\n",
+    "W=(u3-u2)-(u4-u1)#..................#Work done\n",
+    "Qa=(u3-u2)#..........................#Heat added\n",
+    "eta=W/Qa#...........................#Cycle efficiency\n",
+    "print \"The cycle work = %0.2f kJ/kg \"%W\n",
+    "print \"The cycle efficiency = %0.2f %%\"%(eta*100)"
+   ]
+  }
+ ],
+ "metadata": {
+  "kernelspec": {
+   "display_name": "Python 2",
+   "language": "python",
+   "name": "python2"
+  },
+  "language_info": {
+   "codemirror_mode": {
+    "name": "ipython",
+    "version": 2
+   },
+   "file_extension": ".py",
+   "mimetype": "text/x-python",
+   "name": "python",
+   "nbconvert_exporter": "python",
+   "pygments_lexer": "ipython2",
+   "version": "2.7.9"
+  }
+ },
+ "nbformat": 4,
+ "nbformat_minor": 0
+}
diff --git a/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER5_2.ipynb b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER5_2.ipynb
new file mode 100644
index 00000000..522e0194
--- /dev/null
+++ b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER5_2.ipynb
@@ -0,0 +1,119 @@
+{
+ "cells": [
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "# CHAPTER 5 - Combustion in S.I. Engines"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 5.1 PAGE 218"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 2,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Time for one combustion process = 4.51e-03 seconds \n",
+      "The crank position is = 12.47 degree\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "d=10.2#............#Engine bore in cm\n",
+    "spo=0.6#............#Spark plug offset in cm\n",
+    "vf=15.8#............#Average flame speed in m/s\n",
+    "thetas=20#.............#The angle of the crank when spark plug is fired\n",
+    "theta=6.5#..........#Angle by which the Engine rotates for combustion to develop (degree)\n",
+    "N=1200#................#Engine rpm\n",
+    "#calculations\n",
+    "dmax=(0.5*d)+spo#.........#Max distance of flame travel in cm\n",
+    "tf=(dmax)/(vf*100)#................#Time of flame travel in seconds\n",
+    "degs=(N/60)*360#...................#Conversion of engine rpm into degree/second\n",
+    "ctheta=tf*degs#...............#Crank angle for flame travel in degree\n",
+    "tc=theta/degs#..................#time for combustion to develop in seconds\n",
+    "top=tf+tc#......................#Time for one combustion process in seconds\n",
+    "thetatot=theta+ctheta#................#Total crank rotation in degree\n",
+    "thetacp = thetatot-thetas#..........#Crank position\n",
+    "print \"Time for one combustion process = %0.2e seconds \"%top\n",
+    "print \"The crank position is = %0.2f degree\"%thetacp"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 5.2 PAGE 219"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 3,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The time of spark = 15.00 Degrees before TDC \n",
+      "Time of spark = 16.54 degrees before TDC\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "# Initialisation of Variables\n",
+    "dp=22#............#Delay period in degree\n",
+    "cp=17#...............#Combustion period in degree\n",
+    "dper=14#...............#Delay Percentage\n",
+    "#Calculations\n",
+    "thetad=dp/2#.........#Full throttle half speed will result in delay angle being reduced for the same time\n",
+    "#Thus ignition timing should be arranged so that the total of thetad+cp ends 13 degree after TDC\n",
+    "tsp=(thetad+cp)-13#............#Time of spark in degree\n",
+    "print \"The time of spark = %0.2f Degrees before TDC \"%tsp\n",
+    "#Half throttle half speed will result in an increase of 14% in delay time over that at full throttle half speed \n",
+    "theta=(dper*thetad)/100#\n",
+    "dtheta=thetad+theta#............#Delay angle\n",
+    "tp=dtheta+cp#................#Total period\n",
+    "tsp=tp-13#..............#\n",
+    "print \"Time of spark = %0.2f degrees before TDC\"%tsp"
+   ]
+  }
+ ],
+ "metadata": {
+  "kernelspec": {
+   "display_name": "Python 2",
+   "language": "python",
+   "name": "python2"
+  },
+  "language_info": {
+   "codemirror_mode": {
+    "name": "ipython",
+    "version": 2
+   },
+   "file_extension": ".py",
+   "mimetype": "text/x-python",
+   "name": "python",
+   "nbconvert_exporter": "python",
+   "pygments_lexer": "ipython2",
+   "version": "2.7.9"
+  }
+ },
+ "nbformat": 4,
+ "nbformat_minor": 0
+}
diff --git a/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER7_2.ipynb b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER7_2.ipynb
new file mode 100644
index 00000000..79ef34ae
--- /dev/null
+++ b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/CHAPTER7_2.ipynb
@@ -0,0 +1,612 @@
+{
+ "cells": [
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "# CHAPTER 7 - Air capacity of four stroke engines"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 7.1 PAGE 246"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 4,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Gas Inhaled per minute : 0.23 m**3/min \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import pi\n",
+    "# Initialisation of Variables\n",
+    "D=20.3#................#Diameter in cm\n",
+    "L=30.5#.................#Length in cm\n",
+    "N=300#................#Engine rpm\n",
+    "eta=78#.................#Efficiency in percentage\n",
+    "afr=4/1#.................#Air Fuel Ratio\n",
+    "\n",
+    "#Calculations\n",
+    "StV = ((pi)/4)*((D/100)**2)*(L/100)#.......#Calculating the stroke volume\n",
+    "Vinh= (eta/100)*StV#...................#Volume Inhaled\n",
+    "Gainh= (Vinh/(4+1))#..............#Gas Inhaled\n",
+    "Gainhpm = Gainh*(N/2)#\n",
+    "print \"Gas Inhaled per minute : %0.2f m**3/min \"%(Gainhpm)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 7.2 PAGE 247"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 9,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "Volumetric efficiency of the engine is : 0.85\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "#Initializing the variables\n",
+    "\n",
+    "N=3600#................#engine rpm\n",
+    "T=15#................#Inlet temperature in degree Celsius\n",
+    "Tk = T+273#..............#Inlet temperature in Kelvin\n",
+    "p=760#................#Inlet pressure in mm of Hg i.e. 1.013 x 10**5 Pa\n",
+    "ppa=1.013*(10**5)#.........# Inlet pressure in Pascals\n",
+    "pdv=4066#..............#Total piston displacement volume in cm**3\n",
+    "pdvsi=pdv*(10**(-6))#.............#Total piston displacement volume in m**3\n",
+    "afr=14/1#...................#Air fuel ratio is 14:1\n",
+    "bsfc=0.38#..................# b.s.f.c in kg/kWh\n",
+    "BP=86#.............#power output in kW\n",
+    "R=287#................#Gas constant for air in J/kg.K\n",
+    "#Calculations\n",
+    "m = (BP*bsfc*afr)/60#...............#Air consumption\n",
+    "V = (m*R*Tk)/ppa#\n",
+    "DV= pdvsi*(N/2)#.........#Displacement Volume\n",
+    "VE=V/DV#...............#Volumetric Efficiency\n",
+    "print \"Volumetric efficiency of the engine is : %0.2f\"%(VE)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 7.3 PAGE 248"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 1,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The volumetric efficiency based on the free air condition : 0.86\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt,pi\n",
+    "#Initializing the variables\n",
+    "n=4#..............#No of cylinders\n",
+    "d=5#.............#diameter of orifice in cm\n",
+    "dsi=d/100#..........# diameter in m\n",
+    "Cd=0.6#.............#Co-efficient of discharge\n",
+    "D=10#..............#Engine bore in cm\n",
+    "Dsi=d/100#............#Engine bore in m\n",
+    "L=12#................#Engine stroke in cm\n",
+    "Lsi=L/100#............#Engine stroke in m\n",
+    "N=1200#...............#Engine rpm\n",
+    "hw=0.046#............#Pressure drop across orifice in m of water\n",
+    "T = 17#..........#Ambient Temparature in Degree Celsius\n",
+    "Tk = T+273#..........# Ambient Temperature in Kelvin\n",
+    "Pbar = 1#.............# Ambient pressure in bar\n",
+    "Ppa = 1 * (10**5)#.......#Ambient pressure in Pascal\n",
+    "R = 287#.............# Gas constant in J/kg.K\n",
+    "rhow = 1000#............#Density of water in kg/m**3\n",
+    "g=9.81#...............#Acceleration due to gravity\n",
+    "#Calculations\n",
+    "\n",
+    "rhoa= Ppa/(R*Tk)#.........#Density of air\n",
+    "ha= (hw*rhow)/rhoa#\n",
+    "av= sqrt(2*g*ha)#.............#Air velocity\n",
+    "area = (pi/4)*(dsi**2)#\n",
+    "Vact = Cd*area*av#.............# V actual\n",
+    "Vswt = n*(pi/4)*(Dsi**2)*Lsi*(N/60*2)#\n",
+    "eff = Vact/Vswt#...............#Volumetric efficiency\n",
+    "print \"The volumetric efficiency based on the free air condition : %0.2f\"%(eff)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 7.4 PAGE 249"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 1,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The given fuel C7H16 requires 11(O2) for complete combustion\n",
+      "Hence, Mass of fuel is : 100.00\n",
+      "Mass of Oxygen required is : 352.00\n",
+      "The air fuel ratio is : 15.30\n",
+      "The volumetric efficiency of the engine is = 75.90 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "#Initializing the variables\n",
+    "n=1#...................#No of cylinders\n",
+    "k=0.5#\n",
+    "Vs=7000#............#displacement volume in cm**3\n",
+    "Vssi= Vs*(10**(-6))#........#displacement volume in m**3\n",
+    "OP=14.7#...................#Power developed in kW\n",
+    "N=450#..................#Engine rpm\n",
+    "sfc=0.272#................#Specific fuel consumption in kg/kWh\n",
+    "#Fuel used is C7H16\n",
+    "mC=12#.............#mass of carbon in amu\n",
+    "mH=1#.................#mass of hydrogen in amu\n",
+    "mO=16#.................#mass of oxygen in amu\n",
+    "pi=1.013 * (10**5)#................#initial pressure in pascal\n",
+    "T=30#...................#initial temperature in degree celsius\n",
+    "Tk=30+273#................#initial temperature in degree kelvin\n",
+    "R=287#..................#Gas constant for air in J/kg.K\n",
+    "#calculations\n",
+    "print \"The given fuel C7H16 requires 11(O2) for complete combustion\"\n",
+    "mf=(7*mC)+(16*mH)#\n",
+    "print \"Hence, Mass of fuel is : %0.2f\"%(mf)\n",
+    "MO=11* 2 * mO#\n",
+    "print \"Mass of Oxygen required is : %0.2f\"%(MO)\n",
+    "ma = MO/0.23#.......#mass of air\n",
+    "#Air contains 23% of oxygen by weight\n",
+    "afr = ma/mf#...............#air fuel ratio is the ratio of mass of air to mass of fuel\n",
+    "print \"The air fuel ratio is : %0.2f\"%(afr)\n",
+    "MF = sfc * OP#...........#actual fuel consumed in kg/h\n",
+    "MA = afr*MF#\n",
+    "AAS = MA * (1+0.3)#....................#actual air supplied in kg/h\n",
+    "M = AAS + MF#................#mass of charge in kg/h\n",
+    "VCS = ((M/60)*R*Tk)/pi#.............#Volume of charge sucked in m**3/min\n",
+    "DVM = Vssi * (N/2)#..............#Displacement volume/min\n",
+    "eta = VCS/DVM#\n",
+    "print \"The volumetric efficiency of the engine is = %0.2f %%\"%(eta*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 7.5 PAGE 250"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 2,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The volumetric efficiency is = 87.43 %\n",
+      "The brake thermal efficiency is = 23.38 %\n",
+      "The brake torque = 0.01 Nm \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "#Initializing the variables\n",
+    "n=6#................#No of cylinders\n",
+    "vsi=730*(10**(-6))#..........#Piston displacement per cylinder in m**3\n",
+    "BP=80#.............#Power produced per cylinder in kW\n",
+    "N=3100#...........#Engine rpm\n",
+    "C=44*(10**6)#...........#Calorific value of petrol in J/kg\n",
+    "Pc=28#........#Petrol consumed per hour in kg\n",
+    "afr = 13/1#.......#air fuel ratio\n",
+    "pi=0.88*(10**5)#..............#Intake pressure in pa\n",
+    "T=300#............#Intake temperature in Kelvin\n",
+    "R = 287#.........#gas constant in J/kg.K\n",
+    "#calculations\n",
+    "ma = (Pc*afr)/60#...........#air comsumed\n",
+    "rhoa = pi/(R*T)#.......#Density of air\n",
+    "etaV=ma/(rhoa*vsi*n*(N/2))#\n",
+    "print \"The volumetric efficiency is = %0.2f %%\"%(etaV*100)\n",
+    "mf = Pc/3600#...............#Fuel consumed per sec\n",
+    "etaBT = (BP*1000)/(mf*C)#\n",
+    "print \"The brake thermal efficiency is = %0.2f %%\"%(etaBT*100)\n",
+    "T=(BP*60*1000)/(2*(pi)*N)#\n",
+    "print \"The brake torque = %0.2f Nm \"%(T)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 7.6 PAGE 251"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 3,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The volumetric efficiency is = 81.44 %\n",
+      "Percentage Reduction in Output = 4.61 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt\n",
+    "#Initializing the variables\n",
+    "etaV1 = 0.8#.........#Volumetric efficiency\n",
+    "pi1 = 1.013#.......#Inlet pressure\n",
+    "pe1= 1.013\n",
+    "pi2= 1.013#\n",
+    "pe2 = 1.15#.........#Exhaust pressure\n",
+    "Tk1 = 298#...........#Temperature in Kelvin\n",
+    "Tk2 = 318#...........#Temperature in Kelvin\n",
+    "r = 7.5#........#compression ratio\n",
+    "ga=1.4#..........#degree of freedom for gas\n",
+    "#calculations\n",
+    "#For pressure change\n",
+    "eta_V2 = r - (pe2/pi2)**(1/ga)#\n",
+    "eta_V1 = r - (pe1/pi1)**(1/ga)#\n",
+    "x=eta_V2/eta_V1#\n",
+    "#For inlet temperature change\n",
+    "y = sqrt(Tk2/Tk1)#\n",
+    "#For volumetric efficiency, considering both pressure and temperature\n",
+    "etaV2 = etaV1*x*y#\n",
+    "print \"The volumetric efficiency is = %0.2f %%\"%(etaV2*100)\n",
+    "PO=((etaV1/Tk1)-(etaV2/Tk2))/(etaV1/Tk1)#\n",
+    "print \"Percentage Reduction in Output = %0.2f %%\"%(PO*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 7.7 PAGE 252"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 4,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The percentage increase in volumetric efficiency is = 6.68 %\n",
+      "The percentage increase in power = 23.34 %\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt\n",
+    "#Initializing the variables\n",
+    "pi1 = 1.013#.......#Inlet pressure\n",
+    "pe1= 1.013\n",
+    "pi2= 1.3#\n",
+    "pe2 = 1.013#.........#Exhaust pressure\n",
+    "Tk1 = 300#...........#Temperature in Kelvin\n",
+    "Tk2 = 333#...........#Temperature in Kelvin\n",
+    "r = 14#........#compression ratio\n",
+    "ga=1.4#..........#degree of freedom for gas\n",
+    "R=287#...........#gas constant in J/kg.K\n",
+    "#calculations\n",
+    "#For pressure change\n",
+    "eta_V2 = r - (pe2/pi2)**(1/ga)#\n",
+    "eta_V1 = r - (pe1/pi1)**(1/ga)#\n",
+    "x=eta_V2/eta_V1#\n",
+    "#For inlet temperature change\n",
+    "y = sqrt(Tk2/Tk1)#\n",
+    "#For volumetric efficiency, considering both pressure and temperature\n",
+    "pive = ((x*y)-1)#.........#percentage increase in volumetric efficiency\n",
+    "print \"The percentage increase in volumetric efficiency is = %0.2f %%\"%(pive*100)\n",
+    "rho1 = (pi1*10**5)/(R*Tk1)#\n",
+    "rho2 = (pi2*10**5)/(R*Tk2)#\n",
+    "z = (rho2/rho1)*x*y#\n",
+    "pip = (z-1)#\n",
+    "print \"The percentage increase in power = %0.2f %%\"%(pip*100)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 7.8 PAGE 253"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 5,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "There is no change in volumetric efficiency due to inlet and exhaust pressure change\n",
+      "For inlet temperature change\n",
+      "Percentage decrease = 4.99 %\n",
+      "Brake power of the engine on the hill station = 24.81 kW \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt\n",
+    "#Initializing the variables\n",
+    "IP1 = 32#...............#Indicated power output in kW\n",
+    "etamech=80#............#Mechanical efficiency at sea level\n",
+    "p1=1.013#.............#initial pressure at sea level in bar\n",
+    "tk1 = 308#...............#Initial temperature at sea level in Kelvin\n",
+    "tk2 = 278#..................#temperature atop the hill in Kelvin\n",
+    "rhoHg=13600#..............#Density of mercury in kg/m**3\n",
+    "h=2000#.....................#Hill altitude \n",
+    "g = 9.81#................#Acceleration due to gravity\n",
+    "delp = 10#..............#drop of mercury in mm Hg per every 100 m climb\n",
+    "#calculations\n",
+    "\n",
+    "print \"There is no change in volumetric efficiency due to inlet and exhaust pressure change\"\n",
+    "print \"For inlet temperature change\"\n",
+    "x = sqrt(tk2/tk1)#................#for inlet temperature change\n",
+    "#x is the ratio of the efficiencies at the beginning and on hill top\n",
+    "print \"Percentage decrease = %0.2f %%\"%((1-x)*100)\n",
+    "dp = rhoHg*g*((delp/1000)*(h/100))*(10**(-5))#........#Drop in pressure at hill station\n",
+    "p2=p1-dp#\n",
+    "IP_1 = p1/tk1#\n",
+    "IP_2 = (x*p2)/tk2#\n",
+    "k = IP_2/IP_1#..............#Ratio of indicative power output during initial and final conditions\n",
+    "IP2 = (IP1 * k)/(etamech/100)#\n",
+    "#Since the engine speed is the same at two places, the friction and hence mechanical efficiency remains unchanged\n",
+    "BP2 = IP2*(etamech/100)#\n",
+    "print \"Brake power of the engine on the hill station = %0.2f kW \"%(BP2)"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 7.9 PAGE 254"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 6,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The volumetric efficiency of supercharged engine = 86.36 %\n",
+      "Indicated power of supercharged engine is = 102.11 kW \n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt\n",
+    "#Initializing the variables\n",
+    "etaV1 = 0.81#.........#Volumetric efficiency\n",
+    "pi1 = 1.01#.......#Inlet pressure before supercharger\n",
+    "pe1= 1.01#...........#Exhaust pressure before supercharger\n",
+    "pi2= 1.38#............#Inlet pressure after supercharger\n",
+    "pe2 = 1.01#.........#Exhaust pressure in bar after addition of super charger\n",
+    "Tk1 = 300#...........#Temperature in Kelvin\n",
+    "Tk2 = 321#...........#Temperature in Kelvin\n",
+    "r = 7.5#........#compression ratio\n",
+    "ga=1.4#..........#degree of freedom for gas\n",
+    "R=287#.............#Gas constant for air in J/kgK\n",
+    "IP1=75#...............#Indicated power output before addition of supercharger\n",
+    "#calculations\n",
+    "#For pressure change\n",
+    "eta_V2 = r - (pe2/pi2)**(1/ga)#\n",
+    "eta_V1 = r - (pe1/pi1)**(1/ga)#\n",
+    "x=eta_V2/eta_V1#\n",
+    "#For inlet temperature change\n",
+    "y = sqrt(Tk2/Tk1)#\n",
+    "#For volumetric efficiency, considering both pressure and temperature\n",
+    "etaV2 = etaV1*x*y#\n",
+    "print \"The volumetric efficiency of supercharged engine = %0.2f %%\"%(etaV2*100)\n",
+    "rho1 = (pi1*10**5)/(R*Tk1)#....#density of air before addition of supercharger\n",
+    "rho2 = (pi2*10**5)/(R*Tk2)#..#density of air after addition of supercharger\n",
+    "IP2 = IP1 * (etaV2*rho2)/(etaV1*rho1)#\n",
+    "print \"Indicated power of supercharged engine is = %0.2f kW \"%IP2"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 7.10 PAGE 255"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 7,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "The volumetric efficiency of the engine = 72.66 %\n",
+      "The heating value of 1 m**3 of charge at 25 degree Celsius = 1513.16 kJ.m**3\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt,pi\n",
+    "#Initializing the variables\n",
+    "n=1#.....#No of cylinders\n",
+    "D=0.32#.....#Bore of the cylinder in m\n",
+    "L=0.38#......#Stroke of the cylinder in m\n",
+    "N = 280#....#Engine rpm\n",
+    "CV = 18600#....#calorific value of fues in kJ/m**3\n",
+    "Tk1 = 300#....#Initial temperature in Kelvin\n",
+    "p1 = 1.013#.....#Initial pressure in bar\n",
+    "ma = 3.36#.......#mass of air consumed per min\n",
+    "tgc = 0.25#......#test gas consumption in m**3/min\n",
+    "pw = 120#.........#pressure of water in mm during the test gas consumption\n",
+    "tgct = 300#.......#Temperature in Kelvin during test gas consumption\n",
+    "rhow = 1000#.....#density of water in kg/m**3\n",
+    "R=287#...........#Gas constant in J/kg.K\n",
+    "#calculations\n",
+    "V= (ma*R*Tk1)/(p1*(10**5))#...#Volume of air consumed at inlet condition\n",
+    "\n",
+    "gsp = p1 +(pw/rhow)/10.2#...................#Gas supply pressure\n",
+    "#1 bar = 10.2 m\n",
+    "gcic = tgc*(gsp/p1)#..........#Gas consumption at inlet condition\n",
+    "Vi = gcic+V#.....#Volume of mixture at inlet condition\n",
+    "Vswt = (pi/4)*(D**2)*L*(N/2)#......#Swept volume \n",
+    "etaV = Vi/Vswt#.....#Volumetric efficiency\n",
+    "print \"The volumetric efficiency of the engine = %0.2f %%\"%(etaV*100)\n",
+    "hv = (gcic/Vi)*CV#......#Heating value\n",
+    "print \"The heating value of 1 m**3 of charge at 25 degree Celsius = %0.2f kJ.m**3\"%hv"
+   ]
+  },
+  {
+   "cell_type": "markdown",
+   "metadata": {},
+   "source": [
+    "## EXAMPLE 7.12 PAGE 256"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": 8,
+   "metadata": {
+    "collapsed": false
+   },
+   "outputs": [
+    {
+     "name": "stdout",
+     "output_type": "stream",
+     "text": [
+      "(i)Nominal diameter of the inlet valve = 0.04 m or 44.95 mm\n",
+      "(ii)When the engine is modified to develop max indicative power at 2800rpm, nominal diameter of the inlet valve = 0.05 m or 48.55 mm\n",
+      "(iii)The new mach index value is : 0.64\n",
+      "Hence the volumetric efficiency drops (There is a steady decrease in volumetric efficiency of an engine if there is an increase in the mach index beyond 0.55, Refer the FIG 7_12)\n",
+      "(iv)The mach index for the unmodified engine  : 1.10\n",
+      "The volumetric efficiency is approximately 56% (from the FIG 7_12)\n"
+     ]
+    }
+   ],
+   "source": [
+    "from __future__ import division\n",
+    "from math import sqrt,pi\n",
+    "#Initializing the variables\n",
+    "Z=0.55#.............#Mach Index\n",
+    "Dcy=0.11#............#Engine Bore in m\n",
+    "L = 0.14#............#stroke length in m\n",
+    "N = 2400#.............#Engine rpm\n",
+    "N1 = 2800#............#Engine rpm after modification\n",
+    "N2=4800#.............#Max rpm for unmodified engine\n",
+    "p = 0.88#.........#pressure at intake valve in bar\n",
+    "t=340#...............#temperature at intake valve in Kelvin\n",
+    "ki = 0.33#...........#Inlet flow co-efficient\n",
+    "ga = 1.4#...............#degree of freedom of the gas\n",
+    "R = 287#.................#Gas constant for air in J/kg.K\n",
+    "#calculations\n",
+    "\n",
+    "Us = sqrt(ga*R*t)#......#sonic velocity of air-fuel mixture at the inlet valve\n",
+    "Up = (2*L*N)/60#...........#piston speed\n",
+    "Div = sqrt(((Dcy**2)*Up)/(Z*ki*Us))#...............#Nominal diameter of the inlet valve in m\n",
+    "print \"(i)Nominal diameter of the inlet valve = %0.2f m or %0.2f mm\"%(Div,Div*1000)\n",
+    "Div1 = sqrt(((Dcy**2)*2*L*N1)/(Z*ki*Us*60))#.......# Nominal diameter of inlet valve for the modified engine in m\n",
+    "print \"(ii)When the engine is modified to develop max indicative power at 2800rpm, nominal diameter of the inlet valve = %0.2f m or %0.2f mm\"%(Div1, Div1*1000,)\n",
+    "Up1=(2*L*N1)/60#............#New piston speed for modified engine\n",
+    "Z1 = ((Dcy/Div)**2)*(Up1/(ki*Us))#\n",
+    "print \"(iii)The new mach index value is : %0.2f\"%(Z1)\n",
+    "print \"Hence the volumetric efficiency drops (There is a steady decrease in volumetric efficiency of an engine if there is an increase in the mach index beyond 0.55, Refer the FIG 7_12)\"\n",
+    "Up2 = (2*L*N2)/60#..............#Piston speed at max rpm for unmodified engine\n",
+    "Z2 = ((Dcy/Div)**2)*(Up2/(ki*Us))#\n",
+    "print \"(iv)The mach index for the unmodified engine  : %0.2f\"%Z2\n",
+    "print \"The volumetric efficiency is approximately 56% (from the FIG 7_12)\""
+   ]
+  }
+ ],
+ "metadata": {
+  "kernelspec": {
+   "display_name": "Python 2",
+   "language": "python",
+   "name": "python2"
+  },
+  "language_info": {
+   "codemirror_mode": {
+    "name": "ipython",
+    "version": 2
+   },
+   "file_extension": ".py",
+   "mimetype": "text/x-python",
+   "name": "python",
+   "nbconvert_exporter": "python",
+   "pygments_lexer": "ipython2",
+   "version": "2.7.9"
+  }
+ },
+ "nbformat": 4,
+ "nbformat_minor": 0
+}
diff --git a/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/screenshots/HeatTransfer(3)_2.png b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/screenshots/HeatTransfer(3)_2.png
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diff --git a/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/screenshots/cycleWorkEff(4)_2.png b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/screenshots/cycleWorkEff(4)_2.png
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diff --git a/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/screenshots/volumetric_Eff(7)_2.png b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/screenshots/volumetric_Eff(7)_2.png
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+++ b/A_textbook_of_Internal_Combustion_Engines_by_R._K._Rajput/screenshots/volumetric_Eff(7)_2.png