Added(A)/Deleted(D) following books

 A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_3rd_Edition_by_Sergio_Franco/chapter10_6.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_3rd_Edition_by_Sergio_Franco/chapter11_6.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_3rd_Edition_by_Sergio_Franco/chapter12_6.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_3rd_Edition_by_Sergio_Franco/chapter13_6.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_3rd_Edition_by_Sergio_Franco/chapter1_13.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_3rd_Edition_by_Sergio_Franco/chapter2_6.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_3rd_Edition_by_Sergio_Franco/chapter3_6.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_3rd_Edition_by_Sergio_Franco/chapter4_6.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_3rd_Edition_by_Sergio_Franco/chapter5_6.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_3rd_Edition_by_Sergio_Franco/chapter6_6.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_3rd_Edition_by_Sergio_Franco/chapter7_6.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_3rd_Edition_by_Sergio_Franco/chapter8_6.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_3rd_Edition_by_Sergio_Franco/chapter9_6.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_by_Sergio_Franco/chapter1.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_by_Sergio_Franco/chapter10.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_by_Sergio_Franco/chapter11.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_by_Sergio_Franco/chapter12.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_by_Sergio_Franco/chapter13.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_by_Sergio_Franco/chapter2.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_by_Sergio_Franco/chapter3.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_by_Sergio_Franco/chapter4.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_by_Sergio_Franco/chapter5.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_by_Sergio_Franco/chapter6.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_by_Sergio_Franco/chapter7.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_by_Sergio_Franco/chapter8.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_by_Sergio_Franco/chapter9.ipynb
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_by_Sergio_Franco/screenshots/Frequency.png
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_by_Sergio_Franco/screenshots/Saturation.png
A  Design_With_Operational_Amplifiers_And_Analog_Integrated_Circuits_by_Sergio_Franco/screenshots/Step.png
A  ENGINEERING_PHYSICS_by_M.ARUMUGAM/README.txt
A  Electronic_Devices_by_S._Sharma/Chapter02.ipynb
A  Electronic_Devices_by_S._Sharma/Chapter03.ipynb
A  Electronic_Devices_by_S._Sharma/Chapter04.ipynb
A  Electronic_Devices_by_S._Sharma/Chapter05.ipynb
A  Electronic_Devices_by_S._Sharma/Chapter06.ipynb
A  Electronic_Devices_by_S._Sharma/Chapter07.ipynb
A  Electronic_Devices_by_S._Sharma/screenshots/Capture1.png
A  Electronic_Devices_by_S._Sharma/screenshots/Capture2.png
A  Electronic_Devices_by_S._Sharma/screenshots/Capture3.png
A  Electronic_Measurements_and_Instrumentation_by_Er.R.K.Rajput/R.K.RAJPUTCHAPTER_12.ipynb
A  Electronic_Measurements_and_Instrumentation_by_Er.R.K.Rajput/R.K.RAJPUTCHAPTER_8.ipynb
A  Electronic_Measurements_and_Instrumentation_by_Er.R.K.Rajput/R.K.RAJPUT_CHAPTER_1__(2).ipynb
A  Electronic_Measurements_and_Instrumentation_by_Er.R.K.Rajput/R.K.RAJPUT_CHAPTER_2__(1).ipynb
A  Electronic_Measurements_and_Instrumentation_by_Er.R.K.Rajput/R.K.RAJPUT_CHAPTER_7.ipynb
A  Electronic_Measurements_and_Instrumentation_by_Er.R.K.Rajput/R.K._RAJPUT_CHAPTER_6.ipynb
A  Electronic_Measurements_and_Instrumentation_by_Er.R.K.Rajput/R.k.Rajput5.ipynb
A  Electronic_Measurements_and_Instrumentation_by_Er.R.K.Rajput/screenshots/r.k.rajput12_2.png
A  Electronic_Measurements_and_Instrumentation_by_Er.R.K.Rajput/screenshots/r.k_rajput_2.png
A  Electronic_Measurements_and_Instrumentation_by_Er.R.K.Rajput/screenshots/r.krajput_2.png
A  Introduction_to_Electric_Drives_by_J._S._Katre/README.txt
A  Manufacturing_Science_by_A._Ghosh_And_A._K._Mallik/ch2_2.ipynb
A  Manufacturing_Science_by_A._Ghosh_And_A._K._Mallik/ch3_2.ipynb
A  Manufacturing_Science_by_A._Ghosh_And_A._K._Mallik/ch4_2.ipynb
A  Manufacturing_Science_by_A._Ghosh_And_A._K._Mallik/ch5_2.ipynb
A  Manufacturing_Science_by_A._Ghosh_And_A._K._Mallik/ch6_2.ipynb
A  Manufacturing_Science_by_A._Ghosh_And_A._K._Mallik/ch7_2.ipynb
A  Manufacturing_Science_by_A._Ghosh_And_A._K._Mallik/screenshots/FricCoeff_2.png
A  Manufacturing_Science_by_A._Ghosh_And_A._K._Mallik/screenshots/fillingtime_2.png
A  Manufacturing_Science_by_A._Ghosh_And_A._K._Mallik/screenshots/millPOwer_2.png
A  Turbomachines_by_A._V._Arasu/Ch1.ipynb
A  Turbomachines_by_A._V._Arasu/Ch2.ipynb
A  Turbomachines_by_A._V._Arasu/Ch3.ipynb
A  Turbomachines_by_A._V._Arasu/Ch4.ipynb
A  Turbomachines_by_A._V._Arasu/Ch5.ipynb
A  Turbomachines_by_A._V._Arasu/Ch6.ipynb
A  Turbomachines_by_A._V._Arasu/Ch7.ipynb
A  Turbomachines_by_A._V._Arasu/Ch8.ipynb
A  Turbomachines_by_A._V._Arasu/Ch9.ipynb
A  Turbomachines_by_A._V._Arasu/screenshots/Ch3BladeAngPowAndPress.png
A  Turbomachines_by_A._V._Arasu/screenshots/Ch4EffPress.png
A  Turbomachines_by_A._V._Arasu/screenshots/Ch5DegofReacNBladeCoeff.png
A  sample_notebooks/ApurvaBhushan/Chapter_1.ipynb
A  "sample_notebooks/ManchukondaLalitha Pujitha/Chpater_1_Gravity.ipynb"

1 files changed, 997 insertions, 0 deletions

diff --git a/Turbomachines_by_A._V._Arasu/Ch4.ipynb b/Turbomachines_by_A._V._Arasu/Ch4.ipynb
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--- /dev/null
+++ b/Turbomachines_by_A._V._Arasu/Ch4.ipynb
@@ -0,0 +1,997 @@
+{
+ "metadata": {
+  "name": "",
+  "signature": "sha256:4faebe859c372462cb5f17df384c957420077f8445fdcb43b3688f5924547a9e"
+ },
+ "nbformat": 3,
+ "nbformat_minor": 0,
+ "worksheets": [
+  {
+   "cells": [
+    {
+     "cell_type": "heading",
+     "level": 1,
+     "metadata": {},
+     "source": [
+      "Chapter 4 - Axial Flow Compressors & Fans"
+     ]
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 4.1 Page 145"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from __future__ import division\n",
+      "from math import tan, pi\n",
+      "#input data\n",
+      "b1=60#The angle made by the relative velocity vector at exit in degree\n",
+      "db=30#The turning angle in degree\n",
+      "dCx=100#The change in the tangential velocities in m/s\n",
+      "DR=0.5#Degree of reaction\n",
+      "N=36000#The speed of the compressor in rpm\n",
+      "D=0.14#Mean blade diameter in m\n",
+      "P1=2#Inlet pressure in bar\n",
+      "T1=330#Inlet temperature in K\n",
+      "b=0.02#Blade height in m\n",
+      "R=287#The universal gas constant in J/kg.K\n",
+      "Cp=1.005#The specific heat of air at constant pressure in kJ/kg.K\n",
+      "r=1.4#The ratio of specific heats of air\n",
+      "\n",
+      "#calculations\n",
+      "b2=b1-db#The angle made by the relative velocity vector at entry in degree\n",
+      "a1=b2#Air flow angle at exit in degree as DR=0.5\n",
+      "U=(3.1415*D*N)/60#The blade mean speed in m/s\n",
+      "T2=((U*dCx)/(Cp*1000))+T1#The exit air temperature in K\n",
+      "P2=P1*(T2/T1)**(r/(r-1))#The exit air pressure in bar\n",
+      "dP=P2-P1#The pressure rise in bar\n",
+      "Ca=(2*U*DR)/(tan(b2*pi/180)+tan(b1*pi/180))#The axial velocity in m/s\n",
+      "A1=3.1415*D*b#The inlet flow area in m**2\n",
+      "d1=(P1*10**5)/(R*T1)#The inlet air density in kg/m**3\n",
+      "m=d1*A1*Ca#The amount of air handled in kg/s\n",
+      "W=m*Cp*(T2-T1)#The power developed in kW\n",
+      "\n",
+      "#output\n",
+      "print '(a)Air flow angle at exit is %3i degree\\n(b)The pressure rise is %3.2f bar\\n(c)The amount of air handled is %3.2f kg/s\\n(d)The power developed is %3.1f kW'%(a1,dP,m,W)\n",
+      "# The answer in the textbook is not correct."
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Air flow angle at exit is  30 degree\n",
+        "(b)The pressure rise is 0.61 bar\n",
+        "(c)The amount of air handled is 2.12 kg/s\n",
+        "(d)The power developed is 56.0 kW\n"
+       ]
+      }
+     ],
+     "prompt_number": 1
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 4.2 Page 147"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import log10\n",
+      "#input data\n",
+      "P01=1#Atmospheric pressure at inlet in bar\n",
+      "T01=291#Atmospheric temperature at inlet in K\n",
+      "T02=438#Total head temperature in delivery pipe in K \n",
+      "P02=3.5#Total head pressure in delivery pipe in bar\n",
+      "P2=3#Staic pressure in delivery pipe in bar\n",
+      "R=287#The universal gas constant in J/kg.K\n",
+      "Cp=1005#The specific heat of air at constant pressure in J/kg.K\n",
+      "r=1.4#The ratio of specific heats of air\n",
+      "\n",
+      "#calculations \n",
+      "T02s=T01*(P02/P01)**((r-1)/r)#Total isentropic head temperature in delivery pipe in K \n",
+      "nc=(T02s-T01)/(T02-T01)#Total head isentropic efficiency\n",
+      "np=((log10(P02/P01))/((r/(r-1))*(log10(T02/T01))))#Polytropic efficiency\n",
+      "T2=T02*(P2/P02)**((r-1)/r)#Static temperature in delivery pipe in K\n",
+      "C2=(2*Cp*(T02-T2))**(1/2)#The air velocity in delivery pipe in m/s\n",
+      "\n",
+      "#output\n",
+      "print '(a)Total head isentropic efficiency is %0.1f %%\\n(b)Polytropic efficiency %0.1f %%\\n(c)The air velocity in delivery pipe is %3.2f m/s'%(nc*100,np*100,C2)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Total head isentropic efficiency is 85.2 %\n",
+        "(b)Polytropic efficiency 87.5 %\n",
+        "(c)The air velocity in delivery pipe is 194.76 m/s\n"
+       ]
+      }
+     ],
+     "prompt_number": 2
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 4.3 Page 148"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import atan, degrees\n",
+      "#input data\n",
+      "N=8#Number of stages\n",
+      "Po=6#Overall pressure ratio \n",
+      "T01=293#Temperature of air at inlet in K\n",
+      "nc=0.9#Overall isentropic efficiency\n",
+      "DR=0.5#Degree of reaction \n",
+      "U=188#Mean blade speed in m/s\n",
+      "Ca=100#Constant axial velocity in m/s\n",
+      "R=287#The universal gas constant in J/kg.K\n",
+      "Cp=1005#The specific heat of air at constant pressure in J/kg.K\n",
+      "r=1.4#The ratio of specific heats of air\n",
+      "\n",
+      "#calculations\n",
+      "T0n1s=T01*(Po)**((r-1)/r)#The isentropic temperature of air leaving compressor stage in K\n",
+      "T0n1=((T0n1s-T01)/nc)+T01#The temperature of air leaving compressor stage in K\n",
+      "dta2ta1=(Cp*(T0n1-T01))/(N*U*Ca)#The difference between tan angles of air exit and inlet\n",
+      "sta1tb1=U/Ca#The sum of tan of angles of air inlet and the angle made by the relative velocity \n",
+      "b1=degrees(atan((dta2ta1+sta1tb1)/2))#The angle made by the relative velocity vector at exit in degree as the DR=1 then a2=b1\n",
+      "a1=degrees(atan(tan(b1*pi/180)-dta2ta1))#Air flow angle at exit in degree\n",
+      "W=Cp*(T0n1-T01)*10**-3#Power required per kg of air/s in kW\n",
+      "\n",
+      "#output\n",
+      "print '(a)Power required is %3.2f kW\\n(b)\\n    (1)Air flow angle at exit is %.f degree \\n    (2)The angle made by the relative velocity vector at exit is %.f degree'%(W,a1,b1)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Power required is 218.73 kW\n",
+        "(b)\n",
+        "    (1)Air flow angle at exit is 12 degree \n",
+        "    (2)The angle made by the relative velocity vector at exit is 59 degree\n"
+       ]
+      }
+     ],
+     "prompt_number": 3
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 4.4 Page 149"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "W=4.5#Power absorbed by the compressor in MW\n",
+      "m=20#Amount of air delivered in kg/s\n",
+      "P01=1#Stagnation pressure of air at inlet in bar\n",
+      "T01=288#Stagnation temperature of air at inlet in K\n",
+      "np=0.9#Polytropic efficiency of compressor\n",
+      "dT0=20#Temperature rise in first stage in K\n",
+      "R=287#The universal gas constant in J/kg.K\n",
+      "Cp=1.005#The specific heat of air at constant pressure in kJ/kg.K\n",
+      "r=1.4#The ratio of specific heats of air\n",
+      "\n",
+      "\n",
+      "#calculations\n",
+      "T02=T01+dT0#Stagnation temperature of air at outlet in K\n",
+      "T0n1=((W*10**3)/(m*Cp))+T01#The temperature of air leaving compressor stage in K\n",
+      "P0n1=P01*(T0n1/T01)**((np*r)/(r-1))#Pressure at compressor outlet in bar\n",
+      "P1=(T02/T01)**((np*r)/(r-1))#The pressure ratio at the first stage \n",
+      "N=((log10(P0n1/P01)/log10(P1)))#Number of stages \n",
+      "T0n1T01=(P0n1/P01)**((r-1)/(np*r))#The temperature ratio at the first stage\n",
+      "T0n1sT01=(P0n1/P01)**((r-1)/r)#The isentropic temperature ratio at the first stage\n",
+      "nc=((T0n1sT01-1)/(T0n1T01-1))#The overall isentropic efficiency\n",
+      "\n",
+      "#output\n",
+      "print '(a)Pressure at compressor outlet is %3.2f bar\\n(b)Number of stages is %3.f\\n(c)The overall isentropic efficiency is %0.1f %%'%(P0n1,N,nc*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Pressure at compressor outlet is 6.12 bar\n",
+        "(b)Number of stages is   9\n",
+        "(c)The overall isentropic efficiency is 87.2 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 4
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 4.5 Page 151"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import log\n",
+      "#input data\n",
+      "DR=0.5#Degree of reaction\n",
+      "b1=44#Blade inlet angle in degree\n",
+      "b2=13#Blade outlet angle in degree\n",
+      "Po=5#The pressure ratio produced by the compressor\n",
+      "nc=0.87#The overall isentropic efficiency\n",
+      "T01=290#Inlet temperature in K\n",
+      "U=180#Mean blade speed in m/s\n",
+      "l=0.85#Work input factor\n",
+      "R=0.287#The universal gas constant in kJ/kg.K\n",
+      "Cp=1005#The specific heat of air at constant pressure in J/kg.K\n",
+      "r=1.4#The ratio of specific heats of air\n",
+      "\n",
+      "#calculations\n",
+      "a2=b1#Air flow angle at entry in degree as DR=0.5\n",
+      "a1=b2#Air flow angle at exit in degree as DR=0.5\n",
+      "T0n1s=T01*(Po)**((r-1)/r)#The isentropic temperature of air leaving compressor stage in K\n",
+      "T0n1=((T0n1s-T01)/nc)+T01#The temperature of air leaving compressor stage in K\n",
+      "Ca=U/(tan(b2*pi/180)+tan(b1*pi/180))#The axial velocity in m/s\n",
+      "N=((Cp*(T0n1-T01))/(l*U*Ca*(tan(a2*pi/180)-tan(a1*pi/180))))#The number of stages \n",
+      "ds=(Cp*(10**-3)*log(T0n1/T01))-(R*log(Po))#Change in entropy in kJ/kg.K\n",
+      "\n",
+      "#output\n",
+      "print '(a)The number of stages are %3.f\\n(b)The change in entropy is %3.3f kJ/kg-K'%(N,ds)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The number of stages are  12\n",
+        "(b)The change in entropy is 0.054 kJ/kg-K\n"
+       ]
+      }
+     ],
+     "prompt_number": 5
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 4.6 Page 152"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "D=0.6#Mean diameter of compressor in m\n",
+      "N=15000#Running speed of the compressor in rpm\n",
+      "dT=30#Actual overall temperature raise in K\n",
+      "PR=1.3#Pressure ratio of all stages\n",
+      "m=57#Mass flow rate of air in kg/s\n",
+      "nm=0.86#Mechanical efficiency\n",
+      "T1=308#Initial temperature in K\n",
+      "T2=328#Temperature at rotor exit in K\n",
+      "r=1.4#The ratio of specific heats of air\n",
+      "Cp=1.005#The specific heat of air at constant pressure in kJ/kg.K\n",
+      "\n",
+      "#calculations\n",
+      "W=m*Cp*dT#Work done in kW\n",
+      "P=W/nm#Power required in kW\n",
+      "ns=((T1*((PR**((r-1)/r))-1))/(dT))#Stage efficiency\n",
+      "R=(T2-T1)/(dT)#Reaction ratio\n",
+      "\n",
+      "#output\n",
+      "print '(a)Power required to drive the compressor is %3.3f kW\\n(b)The stage efficiency is %0.2f %%\\n(c)The degree of reaction is %3.2f'%(P,ns*100,R)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Power required to drive the compressor is 1998.314 kW\n",
+        "(b)The stage efficiency is 79.92 %\n",
+        "(c)The degree of reaction is 0.67\n"
+       ]
+      }
+     ],
+     "prompt_number": 6
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 4.7 Page 153"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "Pr=2#The pressure ratio of first stage\n",
+      "P1=1.01#The inlet pressure in bar\n",
+      "T1=303#The inlet temperature in K\n",
+      "nc=0.83#Overall efficency of the compressor\n",
+      "pi=0.47#The flow coefficient\n",
+      "dCxCa=0.5#Ratio of change of whirl velocity to axial velocity\n",
+      "D=0.5#Mean diameter in m\n",
+      "r=1.4#The ratio of specific heats of air\n",
+      "Cp=1005#The specific heat of air at constant pressure in J/kg.K\n",
+      "\n",
+      "#calculations\n",
+      "dT=T1*((Pr**((r-1)/r))-1)/nc#The Actual overall temperature raise in K\n",
+      "dCx=dCxCa*pi#The change of whirl velocity in m/s\n",
+      "U=(dT*Cp/dCx)**(1/2)#The mean blade speed in m/s\n",
+      "N=(U*60)/(3.1415*D)#Speed at which compressor runs in rpm\n",
+      "Cx2=(U+(dCx*U))/2#The whirl velocity at exit in m/s\n",
+      "Cx1=U-Cx2#The whirl velocity at entry in m/s\n",
+      "Ca=pi*U#The axial velocity in m/s\n",
+      "C1=((Ca**2)+(Cx1**2))**(1/2)#The inlet absolute velocity of air in m/s\n",
+      "\n",
+      "#output\n",
+      "print '(a)The compressor speed is %3i rpm\\n(b)The absolute velocity of air is %3.2f m/s'%(N,C1)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The compressor speed is 22336 rpm\n",
+        "(b)The absolute velocity of air is 354.34 m/s\n"
+       ]
+      }
+     ],
+     "prompt_number": 7
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 4.8 Page 154"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import acos, asin, sin,cos, sqrt, degrees, pi, atan, tan\n",
+      "from __future__ import division\n",
+      "#input data\n",
+      "N=9000#The rotational speed in rpm\n",
+      "dT0=20#The stagnation temperature rise in K\n",
+      "DhDt=0.6#The hub to tip ratio\n",
+      "l=0.94#The work donee factor\n",
+      "ns=0.9#The isentropic efficiency of the stage\n",
+      "C1=150#Inlet velocity in m/s\n",
+      "P01=1#The ambient pressure in bar\n",
+      "T01=300#The ambient temperature in K\n",
+      "Mr1=0.92#Mach number relative to tip \n",
+      "R=287#The universal gas constant in J/kg.K\n",
+      "Cp=1005#The specific heat of air at constant pressure in kJ/kg.K\n",
+      "r=1.4#The ratio of specific heats of air\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "\n",
+      "#calculations\n",
+      "T1=T01-((C1**2)/(2*Cp))#The inlet temperature in K\n",
+      "W1=Mr1*sqrt(r*R*T1)#The relative velocity at entry in m/s\n",
+      "b11=degrees(acos((C1)/(W1)))#The inlet rotor angle at tip in degree\n",
+      "Ut=W1*sin(b11*pi/180)#Tip speed in m/s\n",
+      "rt=(Ut*60)/(2*3.1415*N)#The tip radius in m\n",
+      "b12=degrees(atan((tan(b11*pi/180)))-((Cp*dT0)/(l*Ut*C1)))#The outlet rotor angle at tip in degree\n",
+      "P1=P01*(T1/T01)**(r/(r-1))#The inlet pressure in bar\n",
+      "d1=(P1*10**5)/(R*T1)#The density of air at the entry in kg/m**3\n",
+      "Dt=2*rt#The tip diameter in m\n",
+      "Dh=DhDt*(Dt)#The hub diameter in m\n",
+      "A1=(3.141/4)*((Dt**2)-(Dh**2))#The area of cross section at the entry in m**2\n",
+      "rm=((Dt/2)+(Dh/2))/2#The mean radius in m\n",
+      "h=((Dt/2)-(Dh/2))#The height of the blade in m\n",
+      "A=2*3.1415*rm*h#The area of the cross section in m**2\n",
+      "m=d1*A*C1#The mass flow rate in kg/s\n",
+      "P03P01=(1+((ns*dT0)/T01))**(r/(r-1))#The stagnation pressure ratio \n",
+      "P=m*Cp*dT0*10**-3#The power required in kW\n",
+      "Uh=(3.1415*Dh*N)/60#The hub speed in m/s\n",
+      "b21=degrees(atan(Uh/C1))#The rotor air angle at entry in degree\n",
+      "b22=degrees(atan(tan(b21*pi/180)-((Cp*dT0)/(l*Uh*C1))))#The rotor air angle at exit in degree\n",
+      "\n",
+      "#output\n",
+      "print '(a)\\n    (1)The tip radius is %3.3f m\\n    (2)The rotor entry angle at tip section is %3.1f degree\\n    (3)The rotor exit angle at tip section is %3.2f degree\\n(b)Mass flow entering the stage is %3.3f kg/s\\n(c)\\n    (1)The stagnation pressure ratio is %3.3f\\n    (2)The power required is %3.2f kW\\n(d)\\n    (1)The rotor air angle at entry is %3.2f degree\\n    (2)The rotor air angle at exit is %3.2f degree'%(rt,b11,b12,m,P03P01,P,b21,b22)\n",
+      "#the answer in the textbook is not correct."
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)\n",
+        "    (1)The tip radius is 0.292 m\n",
+        "    (2)The rotor entry angle at tip section is 61.4 degree\n",
+        "    (3)The rotor exit angle at tip section is 31.72 degree\n",
+        "(b)Mass flow entering the stage is 27.152 kg/s\n",
+        "(c)\n",
+        "    (1)The stagnation pressure ratio is 1.226\n",
+        "    (2)The power required is 545.75 kW\n",
+        "(d)\n",
+        "    (1)The rotor air angle at entry is 47.74 degree\n",
+        "    (2)The rotor air angle at exit is 13.35 degree\n"
+       ]
+      }
+     ],
+     "prompt_number": 8
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 4.9 Page 157"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "Ur=150#The blade root velocity in m/s\n",
+      "Um=200#The mean velocity in m/s\n",
+      "Ut=250#The tip velocity in m/s\n",
+      "dT0=20#The total change in temperature in K\n",
+      "Ca=150#The axial velocity in m/s\n",
+      "l=0.93#The work done factor \n",
+      "Rm=0.5#Reaction at mean radius\n",
+      "R=287#The universal gas constant in J/kg.K\n",
+      "Cp=1005#The specific heat of air at constant pressure in J/kg.K\n",
+      "r=1.4#The ratio of specific heats of air\n",
+      "\n",
+      "#calculations\n",
+      "dtb1tb2=((Cp*dT0)/(l*Um*Ca))#The difference between the tangent angles of blade angles at mean\n",
+      "atb1tb2=((2*Rm*Um)/(Ca))#The sum of the tangent angles of blade angles at mean\n",
+      "b1m=degrees(atan((atb1tb2+dtb1tb2)/2))#The inlet blade angle in degree at mean\n",
+      "a2m=b1m#The exit air angle in degree as the Reaction at mean radius is 0.5\n",
+      "b2m=degrees(atan(tan(b1m*pi/180)-dtb1tb2))#The exit blade angle in degree at mean\n",
+      "a1m=b2m#The inlet air angle in degree as the reaction at mean radius is 0.5\n",
+      "rmrh=Um/Ur#The ratio of radii of mean and root velocities at hub\n",
+      "a1h=degrees(atan(tan(a1m*pi/180)*(rmrh)))#The inlet air angle in degree at hub\n",
+      "b1h=degrees(atan((Ur/Ca)-(tan(a1h*pi/180))))#The inlet blade angle in degree at hub\n",
+      "a2h=degrees(atan(tan(a2m*pi/180)*(rmrh)))#The outlet air angle in degree at hub\n",
+      "b2h=degrees(atan((Ur/Ca)-(tan(a2h*pi/180))))#The outlet blade angle in degree at hub\n",
+      "Rh=((Ca*(tan(b1h*pi/180)+tan(b2h*pi/180)))/(2*Ur))#The degree of reaction at the hub\n",
+      "rmrt=Um/Ut#The ratio of radii of mean and tip velocities at tip\n",
+      "a1t=degrees(atan(tan(a1m)*(rmrt)))#The inlet air angle in degree at tip\n",
+      "b1t=degrees(atan((Ut/Ca)-(tan(a1t*pi/180))))#The inlet blade angle in degree at tip\n",
+      "a2t=degrees(atan(tan(a2m)*(rmrt)))#The outlet air angle in degree at tip\n",
+      "b2t=degrees(atan((Ut/Ca)-(tan(a2t*pi/180))))#The outlet blade angle in degree at tip\n",
+      "Rt=((Ca*(tan(b1t*pi/180)+tan(b2t*pi/180)))/(2*Ut))#The degree of reaction at tip\n",
+      "\n",
+      "#output\n",
+      "print '(a)At the mean\\n    (1)The inlet blade angle is %3.2f degree\\n    (2)The inlet air angle is %3.2f degree\\n    (3)The outlet blade angle is %3.2f degree\\n    (4)The outlet air angle is %3.2f degree\\n    (5)Degree of reaction is %3.1f \\n(b)At the root\\n    (1)The inlet blade angle is %3.2f degree\\n    (2)The inlet air angle is %3.2f degree\\n    (3)The outlet blade angle is %3.2f degree\\n    (4)The outlet air angle is %3.2f degree\\n    (5)Degree of reaction is %3.3f\\n(c)At the tip\\n    (1)The inlet blade angle is %3.2f degree\\n    (2)The inlet air angle is %3.2f degree\\n    (3)The outlet blade angle is %3.2f degree\\n    (4)The outlet air angle is %3.2f degree\\n    (5)Degree of reaction is %3.3f\\n'%(b1m,a1m,b2m,a2m,Rm,b1h,a1h,b2h,a2h,Rh,b1t,a1t,b2t,a2t,Rt)\n",
+      "#the answer in the textbook is not correct."
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)At the mean\n",
+        "    (1)The inlet blade angle is 45.76 degree\n",
+        "    (2)The inlet air angle is 17.04 degree\n",
+        "    (3)The outlet blade angle is 17.04 degree\n",
+        "    (4)The outlet air angle is 45.76 degree\n",
+        "    (5)Degree of reaction is 0.5 \n",
+        "(b)At the root\n",
+        "    (1)The inlet blade angle is 30.60 degree\n",
+        "    (2)The inlet air angle is 22.23 degree\n",
+        "    (3)The outlet blade angle is -20.26 degree\n",
+        "    (4)The outlet air angle is 53.86 degree\n",
+        "    (5)Degree of reaction is 0.111\n",
+        "(c)At the tip\n",
+        "    (1)The inlet blade angle is -57.81 degree\n",
+        "    (2)The inlet air angle is 72.92 degree\n",
+        "    (3)The outlet blade angle is 79.66 degree\n",
+        "    (4)The outlet air angle is -75.31 degree\n",
+        "    (5)Degree of reaction is 1.168\n",
+        "\n"
+       ]
+      }
+     ],
+     "prompt_number": 9
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 4.10 Page 160"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "Uh=150#The blade root velocity in m/s\n",
+      "Um=200#The mean velocity in m/s\n",
+      "Ut=250#The tip velocity in m/s\n",
+      "dT0=20#The total change in temperature in K\n",
+      "Ca1m=150#The axial velocity in m/s\n",
+      "l=0.93#The work done factor \n",
+      "Rm=0.5#Reaction at mean radius\n",
+      "N=9000#Rotational speed in rpm\n",
+      "R=287#The universal gas constant in J/kg.K\n",
+      "Cp=1005#The specific heat of air at constant pressure in J/kg.K\n",
+      "r=1.4#The ratio of specific heats of air\n",
+      "\n",
+      "#calculations\n",
+      "dtb1tb2=((Cp*dT0)/(l*Um*Ca1m))#The difference between the tangent angles of blade angles at mean\n",
+      "atb1tb2=((2*Rm*Um)/(Ca1m))#The sum of the tangent angles of blade angles at mean\n",
+      "b1m=degrees(atan((atb1tb2+dtb1tb2)/2))#The inlet blade angle in degree at mean\n",
+      "a2m=b1m#The exit air angle in degree as the Reaction at mean radius is 0.5\n",
+      "b2m=degrees(atan(tan(pi/180*b1m)-dtb1tb2))#The exit blade angle in degree at mean\n",
+      "a1m=b2m#The inlet air angle in degree as the reaction at mean radius is 0.5\n",
+      "Dh=(Uh*60)/(3.141*N)#Hub diameter in m\n",
+      "Dm=(Um*60)/(3.141*N)#Mean diameter in m\n",
+      "Cx1m=Ca1m*tan(pi/180*a1m)#The whirl velocity at inlet at mean in m/s\n",
+      "Cx2m=Ca1m*tan(pi/180*a2m)#The whirl velocity at exit at mean in m/s\n",
+      "Cx1h=(Cx1m*(Dh/2)/(Dm/2))#The whirl velocity at inlet at hub in m/s\n",
+      "Cx2h=(Cx2m*(Dh/2)/(Dm/2))#The whirl velocity at exit at hub in m/s\n",
+      "K1=(Ca1m**2)+(2*(Cx1m**2))#Sectional velocity in m/s\n",
+      "Ca1h=((K1)-(2*(Cx1h**2)))**(1/2)#The axial velocity at hub inlet in (m/s)**2\n",
+      "w=(2*3.141*N)/60#Angular velocity of blade in rad/s\n",
+      "K2=(Ca1m**2)+(2*(Cx2m**2))-(2*((Cx2h/(Dh/2))-(Cx1m/(Dm/2))))*(w*(Dm/2)**(2))#Sectional velocity in (m/s)**2\n",
+      "Ca2h=(K2-(2*Cx2h**2)+(2*((Cx2h/(Dh/2))-(Cx1h/(Dh/2))))*(w*(Dh/2)**(2)))**(1/2)#Axial velocity at hub outlet in m/s\n",
+      "a1h=degrees(atan(Cx1h/Ca1h))#Air angle at inlet in hub in degree\n",
+      "b1h=degrees(atan((Uh-Cx1h)/Ca1h))#Blade angle at inlet in hub in degree\n",
+      "a2h=degrees(atan(Cx2h/Ca2h))#Air angle at exit in hub in degree\n",
+      "b2h=degrees(atan((Uh-Cx2h)/Ca2h))#Blade angle at exit in hub in degree\n",
+      "W1=Ca1h/cos(pi/180*b1h)#Relative velocity at entry in hub in m/s\n",
+      "W2=Ca2h/cos(pi/180*b2h)#Relative velocity at exit in hub in m/s\n",
+      "Rh=((W1**2)-(W2**2))/(2*Uh*(Cx2h-Cx1h))#The degree of reaction at hub\n",
+      "Dt=(Ut*60)/(3.141*N)#Tip diameter in m\n",
+      "Cx1t=(Cx1m*(Dt/2)/(Dm/2))#The whirl velocity at inlet at tip in m/s\n",
+      "Cx2t=(Cx2m*(Dt/2)/(Dm/2))#The whirl velocity at exit at tip in m/s\n",
+      "Ca1t=(K1-(2*Cx1t**2))**(1/2)#Axial velocity at tip inlet in m/s\n",
+      "Ca2t=(K2-(2*Cx2t**2)+(2*((Cx2t/(Dt/2))-(Cx1t/(Dt/2))))*(w*(Dt/2)**(2)))**(1/2)#Axial velocity at tip outlet in m/s\n",
+      "a1t=degrees(atan(Cx1t/Ca1t))#Air angle at inlet in tip in degree\n",
+      "b1t=degrees(atan((Ut-Cx1t)/Ca1t))#Blade angle at inlet in tip in degree\n",
+      "a2t=degrees(atan(Cx2t/Ca2t))#Air angle at exit in tip in degree\n",
+      "b2t=degrees(atan((Ut-Cx2t)/Ca2t))#Blade angle at exit in tip in degree\n",
+      "W1=Ca1t/cos(pi/180*b1t)#Relative velocity at entry in tip in m/s\n",
+      "W2=Ca2t/cos(pi/180*b2t)#Relative velocity at exit in tip in m/s\n",
+      "Rt=((W1**2)-(W2**2))/(2*Ut*(Cx2t-Cx1t))#The degree of reaction at tip\n",
+      "\n",
+      "#output\n",
+      "print '(a)At the mean\\n    (1)The inlet blade angle is %3.2f degree\\n    (2)The inlet air angle is %3.2f degree\\n    (3)The outlet blade angle is %3.2f degree\\n    (4)The outlet air angle is %3.2f degree\\n    (5)Degree of reaction is %3.1f \\n(b)At the root\\n    (1)The inlet blade angle is %3.2f degree\\n    (2)The inlet air angle is %3.1f degree\\n    (3)The outlet blade angle is %3.1f degree\\n    (4)The outlet air angle is %3.1f degree\\n    (5)Degree of reaction is %3.1f\\n(c)At the tip\\n    (1)The inlet blade angle is %3.2f degree\\n    (2)The inlet air angle is %3.2f degree\\n    (3)The outlet blade angle is %3.2f degree\\n    (4)The outlet air angle is %3.2f degree\\n    (5)Degree of reaction is %3.1f\\n'%(b1m,a1m,b2m,a2m,Rm,b1h,a1h,b2h,a2h,Rh,b1t,a1t,b2t,a2t,Rt)\n",
+      "# the answer in the textbook is not correct."
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)At the mean\n",
+        "    (1)The inlet blade angle is 45.76 degree\n",
+        "    (2)The inlet air angle is 17.04 degree\n",
+        "    (3)The outlet blade angle is 17.04 degree\n",
+        "    (4)The outlet air angle is 45.76 degree\n",
+        "    (5)Degree of reaction is 0.5 \n",
+        "(b)At the root\n",
+        "    (1)The inlet blade angle is 36.51 degree\n",
+        "    (2)The inlet air angle is 12.5 degree\n",
+        "    (3)The outlet blade angle is 12.5 degree\n",
+        "    (4)The outlet air angle is 36.5 degree\n",
+        "    (5)Degree of reaction is 0.5\n",
+        "(c)At the tip\n",
+        "    (1)The inlet blade angle is 53.62 degree\n",
+        "    (2)The inlet air angle is 22.05 degree\n",
+        "    (3)The outlet blade angle is 22.05 degree\n",
+        "    (4)The outlet air angle is 53.62 degree\n",
+        "    (5)Degree of reaction is 0.5\n",
+        "\n"
+       ]
+      }
+     ],
+     "prompt_number": 10
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 4.11 Page 163"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "N=3600#Running speed of blower in rpm\n",
+      "Dt=0.2#The rotor  tip diameter in m\n",
+      "Dh=0.125#The rotor hub diameter in m\n",
+      "P1=1.013#The atmospheric pressure in bar\n",
+      "T1=298#The atmospheric temperature in K\n",
+      "m=0.5#Mass flow rate of air in kg/s\n",
+      "db=20#The turning angle of the rotor in degree\n",
+      "b1=55#The inlet blade angle in degree \n",
+      "R=287#The universal gas constant in J/kg.K\n",
+      "nc=0.9#Total-to-total efficiency\n",
+      "P=0.25#Total pressure drop across the intake in cm of water\n",
+      "Cp=1005#The specific heat of air at constant pressure in J/kg.K\n",
+      "r=1.4#The ratio of specific heats of air\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "ns=0.75#The stator efficiency\n",
+      "dw=1000#Density of water in kg/m**3\n",
+      "\n",
+      "#calculations\n",
+      "d1=(P1*10**5)/(R*T1)#The density of air at inlet in kg/m**3\n",
+      "A=(3.141/4)*((Dt**2)-(Dh**2))#The area of flow in m**2\n",
+      "Ca=m/(d1*A)#The axial velocity of air in m/s\n",
+      "U=((3.141*(Dt+Dh)*N)/(2*60))#Mean rotor blade velocity in m/s\n",
+      "b2=b1-db#The outlet blade angle in degree\n",
+      "Cx2=U-(Ca*tan(pi/180*b2))#The whirl velocity at exit in m/s \n",
+      "Cx1=0#The whirl velocity at entry in m/s as flow at inlet is axial \n",
+      "dh0r=U*(Cx2-Cx1)#The actual total enthalpy rise across the rotor in J/kg\n",
+      "dh0sr=nc*dh0r#The isentropic total enthalpy rise across the rotor in J/kg\n",
+      "dP0r=(d1*dh0sr)*((10**-1)/(g))#The total pressure rise across the rotor in cm of water\n",
+      "P0=dP0r-P#Stagnation pressure at the rotor exit in cm of water\n",
+      "C2=((Ca**2)+(Cx2**2))**(1/2)#The absolute velocity at the exit in m/s\n",
+      "dPr=dP0r-((d1*((C2**2)-(Ca**2)))/2)*((10**-1)/g)#The static pressure across the rotor in cm of water\n",
+      "dhs=((C2**2)-(Ca**2))/2#The actual enthalpy change across the stator in J/kg\n",
+      "dhss=ns*dhs#The theoretical enthalpy change across the stator in J/kg\n",
+      "dPs=(d1*dhss)*((10**-1)/g)#The static pressure rise across the stator in cm of water\n",
+      "dP0s=-((dPs/((10**-1)/g))+((d1/2)*(Ca**2-C2**2)))*(10**-1/g)#The change in total pressure across the stator in cm of water\n",
+      "P03=P0-dP0s#Total pressure at stator inlet in cm of water\n",
+      "dh0ss=((dw*g*(P03/100))/d1)#Theoretical total enthalpy change across the stage in J/kg\n",
+      "ntt=dh0ss/dh0r#The overall total-to-total efiiciency\n",
+      "DR=dPr/(dPr+dPs)#The degree of reaction for the stage\n",
+      "\n",
+      "#output\n",
+      "print '(a)Total pressure of air exit of rotor is %3.2f cm of water\\n(b)The static pressure rise across the rotor is %3.2f cm of water\\n(c)The static pressure rise across the stator os %3.2f cm of water\\n(d)The change in total pressure across the stator is %3.2f cm of water\\n(e)The overall total-to-total efficiency is %0.1f %%\\n(f)The degree of reaction for the stage is %0.1f %%'%(P0,dPr,dPs,dP0s,ntt*100,DR*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Total pressure of air exit of rotor is 4.80 cm of water\n",
+        "(b)The static pressure rise across the rotor is 3.66 cm of water\n",
+        "(c)The static pressure rise across the stator os 1.04 cm of water\n",
+        "(d)The change in total pressure across the stator is 0.35 cm of water\n",
+        "(e)The overall total-to-total efficiency is 79.3 %\n",
+        "(f)The degree of reaction for the stage is 77.8 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 11
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 4.12 Page 166"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "Q=2.5#The amount of air which fan takes in m**3/s\n",
+      "P1=1.02#The inlet pressure of air in bar\n",
+      "T1=315#The inlet temperature of air in K\n",
+      "dH=0.75#The pressure head delivered by axial flow fan in m W.G\n",
+      "T2=325#The delivery temperature of air in K\n",
+      "R=287#The universal gas constant in J/kg.K\n",
+      "Cp=1.005#The specific heat of air at constant pressure in kJ/kg.K\n",
+      "r=1.4#The ratio of specific heats of air\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "\n",
+      "#calculations\n",
+      "d=(P1*10**5)/(R*T1)#The density of air in kg/m**3\n",
+      "m=d*Q#The mass flow rate of air in kg/s\n",
+      "W=m*Cp*(T2-T1)#Power required to drive the fan in kW\n",
+      "dP=((10**3)*g*dH)/(10**5)#The overall pressure difference in bar\n",
+      "P2=P1+(dP)#The exit pressure in bar\n",
+      "nf=((T1*(((P2/P1)**((r-1)/r))-1))/(T2-T1))#Static fan efficiency\n",
+      "\n",
+      "#output\n",
+      "print '(a)Mass flow rate through the fan is %3.2f kg/s\\n(b)Power required to drive the fan is %3.2f kW\\n(c)Static fan efficiency is %0.2f %%'%(m,W,nf*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Mass flow rate through the fan is 2.82 kg/s\n",
+        "(b)Power required to drive the fan is 28.35 kW\n",
+        "(c)Static fan efficiency is 63.31 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 12
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 4.13 Page 167"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "b2=10#Rotor blade air angle at exit in degree\n",
+      "Dt=0.6#The tip diameter in m\n",
+      "Dh=0.3#The hub diameter in m\n",
+      "N=960#The speed of the fan in rpm\n",
+      "P=1#Power required by the fan in kW\n",
+      "pi=0.245#The flow coefficient\n",
+      "P1=1.02#The inlet pressure in bar\n",
+      "T1=316#The inlet temperature in K\n",
+      "R=287#The universal gas constant in J/kg.K\n",
+      "Cp=1.005#The specific heat of air at constant pressure in kJ/kg.K\n",
+      "r=1.4#The ratio of specific heats of air\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "\n",
+      "#calculations\n",
+      "A=(3.141/4)*((Dt**2)-(Dh**2))#Area of the fan at inlet in m**2\n",
+      "Dm=(Dt+Dh)/2#The mean rotor diameter in m\n",
+      "U=(3.141*Dm*N)/60#The mean blade speed in m/s\n",
+      "Ca=pi*U#The axial velocity in m/s\n",
+      "Q=A*Ca#The flow rate of air in m**3/s\n",
+      "d=(P1*10**5)/(R*T1)#Density of air in kg/m**3\n",
+      "dPst=((d*(U**2)*(1-((pi*tan(pi/180*b2))**2)))/2)*((10**5)/(g*(10**3)))*10**-5#Static pressure across the stage in m W.G\n",
+      "Wm=U*(U-(Ca*tan(pi/180*b2)))#Work done per unit mass in J/kg\n",
+      "m=d*Q#Mass flow rate in kg/s\n",
+      "W=m*Wm#Work done in W\n",
+      "no=W/(P*10**3)#Overall efficiency \n",
+      "\n",
+      "#output\n",
+      "print '(a)THe flow rate is %3.3f m**3/s\\n(b)Static pressure rise across the stage is %3.3f m W.G\\n(c)The overall efficiency is %0.2f %%'%(Q,dPst,no*100)\n",
+      "# the answer for last part is not accurate."
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)THe flow rate is 1.175 m**3/s\n",
+        "(b)Static pressure rise across the stage is 0.029 m W.G\n",
+        "(c)The overall efficiency is 67.35 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 13
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 4.14 Page 169"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "b2=10#Rotor blade air angle at exit in degree\n",
+      "Dt=0.6#The tip diameter in m\n",
+      "Dh=0.3#The hub diameter in m\n",
+      "N=960#The speed of the fan in rpm\n",
+      "P=1#Power required by the fan in kW\n",
+      "pi=0.245#The flow coefficient\n",
+      "P1=1.02#The inlet pressure in bar\n",
+      "T1=316#The inlet temperature in K\n",
+      "R=287#The universal gas constant in J/kg.K\n",
+      "Cp=1.005#The specific heat of air at constant pressure in kJ/kg.K\n",
+      "r=1.4#The ratio of specific heats of air\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "\n",
+      "#calculations\n",
+      "A=(3.141/4)*((Dt**2)-(Dh**2))#Area of the fan at inlet in m**2\n",
+      "Dm=(Dt+Dh)/2#The mean rotor diameter in m\n",
+      "U=(3.141*Dm*N)/60#The mean blade speed in m/s\n",
+      "Ca=pi*U#The axial velocity in m/s\n",
+      "Q=A*Ca#The flow rate of air in m**3/s\n",
+      "d=(P1*10**5)/(R*T1)#Density of air in kg/m**3\n",
+      "b1=degrees(atan(U/Ca))#Rotor blade angle at entry in degree\n",
+      "dPst=((d*(U**2)*(1-((pi*tan(pi/180*b2))**2)))/2)#Static pressure rise across the stage in N/m**2\n",
+      "dPr=dPst#Static pressure rise across the rotor in N/m**2\n",
+      "Wm=U*(U-(Ca*tan(pi/180*b2)))#Work done per unit mass in J/kg\n",
+      "dP0st=d*Wm#Stagnation pressure of the stage in N/m**2\n",
+      "DR1=dPr/dP0st#Degree of reaction\n",
+      "DR2=(Ca/(2*U))*(tan(pi/180*b1)+tan(pi/180*b2))#Degree of reaction\n",
+      "\n",
+      "#output\n",
+      "print '(a)Rotor blade angle at entry is %3.2f degree\\n(b)Degree of reaction is %0.1f %%'%(b1,DR1*100)\n",
+      "# the answer for last part is not correct in the textbook."
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Rotor blade angle at entry is 76.23 degree\n",
+        "(b)Degree of reaction is 50.2 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 14
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 4.15 Page 170"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "m=3#Mass flow rate of air in kg/s\n",
+      "P1=100*10**3#The atmospheric pressure in Pa\n",
+      "T1=310#The atmospheric temperature in K\n",
+      "nb=0.8#The efficiency of the blower\n",
+      "nm=0.85#The mechanical efficiency\n",
+      "P=30#The power input in kW\n",
+      "R=287#The universal gas constant in J/kg.K\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "dw=1000#Density of water in kg/m**3\n",
+      "\n",
+      "#calculations\n",
+      "no=nb*nm#Overall efficiency of the blower\n",
+      "d=(P1)/(R*T1)#The density of the air in kg/m**3\n",
+      "dP=((no*P*10**3)/m)*d#The pressure developed in N/m**2\n",
+      "dH=((dP)/(g*dw))*(10**3)#The pressure developed in mm W.G\n",
+      "\n",
+      "#output\n",
+      "print '(a)Overall efficiency of the blower is %3.2f\\n(b)The pressure developed is %3.2f mm W.G'%(no,dH)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Overall efficiency of the blower is 0.68\n",
+        "(b)The pressure developed is 779.11 mm W.G\n"
+       ]
+      }
+     ],
+     "prompt_number": 15
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 4.16 Page 170"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "psi=0.4#Pressure coefficient \n",
+      "m=3.5#Mass flow rate of air in kg/s\n",
+      "N=750#The speed of fan in rpm\n",
+      "T1=308#The static temperature at the entry in K\n",
+      "Dh=0.26#The hub diameter in m\n",
+      "DhDt=1/3#The hub to tip ratio\n",
+      "P1=98.4*10**3#The static pressure at entry in Pa\n",
+      "nm=0.9#The mechanical efficiency\n",
+      "nf=0.79#Static fan efficiency\n",
+      "R=287#The universal gas constant in J/kg.K\n",
+      "Cp=1.005#The specific heat of air at constant pressure in kJ/kg.K\n",
+      "r=1.4#The ratio of specific heats of air\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "dw=1000#Density of water in kg/m**3\n",
+      "\n",
+      "#calculations\n",
+      "no=nm*nf#Overall efficiency\n",
+      "Dt=Dh/DhDt#The tip diameter in m\n",
+      "Dm=(Dt+Dh)/2#Mean rotor diameter in m\n",
+      "U=(3.141*Dm*N)/60#The mean blade speed in m/s\n",
+      "dPd=((U**2)/2)*psi#The ratio of change in pressure to density in J/kg\n",
+      "Wi=dPd*m#The ideal work in W\n",
+      "P=Wi/nm#The power required by the fan in W\n",
+      "d=P1/(R*T1)#The density of the air in kg/m**3\n",
+      "A=(3.141/4)*((Dt**2)-(Dh**2))#Area of cross section of the fan in m**2\n",
+      "Ca=m/(d*A)#The axial velocity of air in m/s\n",
+      "pi=Ca/U#The flow coefficient\n",
+      "tb1tb2=psi/(2*pi)#The difference between tangent angles of rotor inlet and exit angles\n",
+      "b2=degrees(atan((1-(dPd/U**2))/pi))#The exit rotor angle in degree\n",
+      "b1=degrees(atan((tan(b2*pi/180))+(tb1tb2)))#The inlet rotor angle in degree\n",
+      "dP=d*dPd#The pressure developed in N/m**2\n",
+      "dH=(dP/(dw*g))*10**3#Pressure developed in mm of W.G\n",
+      "\n",
+      "#output\n",
+      "print '(a)The overall efficiency is %0.1f %%\\n(b)The power required by the fan is %3.2f W\\n(c)The flow coefficient is %3.2f\\n(d)\\n    (1)The rotor inlet angle is %3.2f degree\\n    (2)The rotor exit angle is %3.2f degree\\n(e)The pressure developed is %3.2f mm of W.G'%(no*100,P,pi,b1,b2,dH)\n",
+      "# the answer for part(d) is not correct in the textbook."
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The overall efficiency is 71.1 %\n",
+        "(b)The power required by the fan is 324.20 W\n",
+        "(c)The flow coefficient is 0.36\n",
+        "(d)\n",
+        "    (1)The rotor inlet angle is 34.39 degree\n",
+        "    (2)The rotor exit angle is 65.62 degree\n",
+        "(e)The pressure developed is 9.46 mm of W.G\n"
+       ]
+      }
+     ],
+     "prompt_number": 16
+    }
+   ],
+   "metadata": {}
+  }
+ ]
+}
\ No newline at end of file