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"

12 files changed, 7250 insertions, 0 deletions

diff --git a/Turbomachines_by_A._V._Arasu/Ch1.ipynb b/Turbomachines_by_A._V._Arasu/Ch1.ipynb
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--- /dev/null
+++ b/Turbomachines_by_A._V._Arasu/Ch1.ipynb
@@ -0,0 +1,709 @@
+{
+ "metadata": {
+  "name": "",
+  "signature": "sha256:04fae3340038d72ec2280e59669f4edde21c4cc5f0e44781b3f3472ae74ef696"
+ },
+ "nbformat": 3,
+ "nbformat_minor": 0,
+ "worksheets": [
+  {
+   "cells": [
+    {
+     "cell_type": "heading",
+     "level": 1,
+     "metadata": {},
+     "source": [
+      "Chapter1 - Basic Concepts of Turbo Machines"
+     ]
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex-1.1 Page 18"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from __future__ import division\n",
+      "#input data\n",
+      "P01=1#initial pressure of a fluid in bar\n",
+      "P02=10#final pressure of a fliud in bar\n",
+      "T01=283#initial total temperature in K\n",
+      "ntt=0.75#total-to-total efficiency\n",
+      "d=1000#density of water in kg/m**3\n",
+      "r=1.4#ratio of specific heats for air\n",
+      "Cp=1.005#specific at heat at constant pressure in kJ/kg.K\n",
+      "\n",
+      "#calculations\n",
+      "h0s1=(1/d)*(P02-P01)*10**2#enthalpy in kJ/kg\n",
+      "h01=(h0s1/ntt)#enthalpy in kJ/kg\n",
+      "T02s=T01*(P02/P01)**((r-1)/r)#temperature in K\n",
+      "h0s2=(Cp*(T02s-T01))#enthalpy in kJ/kg\n",
+      "h02=(h0s2/ntt)#enthalpy in kJ/kg\n",
+      "\n",
+      "#output\n",
+      "print '''The work of compression for adiabatic steady flow per kg of fliud if - \n",
+      "(a)The fliud is liquid water is %3.1f kJ/kg\n",
+      "(b)The fliud is air as a perfect gas is %3.2f kJ/kg'''%(h01,h02)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "The work of compression for adiabatic steady flow per kg of fliud if - \n",
+        "(a)The fliud is liquid water is 1.2 kJ/kg\n",
+        "(b)The fliud is air as a perfect gas is 352.94 kJ/kg\n"
+       ]
+      }
+     ],
+     "prompt_number": 1
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 1.2 Page 19"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "\n",
+      "#input data\n",
+      "P01=7#Total initial pressure of gases at entry in bar\n",
+      "T01=1100#Total initial temperature in K\n",
+      "P02=1.5#Total final pressure of gases at exit in bar\n",
+      "T02=830#Total final temperature in K\n",
+      "C2=250#Exit velocity in m/s\n",
+      "r=1.3#Ratio of specific heats of gases\n",
+      "M=28.7#Molecular weight of gases\n",
+      "R1=8.314#Gas constant of air in kJ/kg.K\n",
+      "\n",
+      "#calculations\n",
+      "T02s=T01*(P02/P01)**((r-1)/r)#Final temperature in K\n",
+      "ntt=((T01-T02)/(T01-T02s))#Total-to-total efficiency\n",
+      "R=(R1/M)#Gas constant of given gas in kJ/kg.K\n",
+      "Cp=((r*R)/(r-1))#Specific heat of given gas at constant pressure in kJ/kg.K\n",
+      "T2s=(T02s-((C2**2)/(2*Cp*1000)))#Temperature in isentropic process at exit in K\n",
+      "nts=((T01-T02)/(T01-T2s))#Total-to-static efficiency\n",
+      "\n",
+      "#output\n",
+      "print '''The total-to-total efficiency of gases is %0.2f %%\n",
+      "The total-to-static efficiency of gases is %0.1f %%'''%(ntt*100,nts*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "The total-to-total efficiency of gases is 82.05 %\n",
+        "The total-to-static efficiency of gases is 76.3 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 2
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 1.3 Page 20"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "h0=6#Change in total enthalpy in kJ/kg\n",
+      "T01=303#Total inlet temperature of fluid in K\n",
+      "P01=1#Total inlet pressure of fliud in bar\n",
+      "Cp=1.005#specific at heat at constant pressure in kJ/kg.K\n",
+      "ntt=0.75#Adiabatic total-to-total efficiency\n",
+      "r=1.4#ratio of specific heats for air\n",
+      "\n",
+      "#calculations\n",
+      "T02=T01+(h0/Cp)#Exit total termperature of fliud in K\n",
+      "P1=(1+((ntt*h0)/(Cp*T01)))**(r/(r-1))#Total pressure ratio of fluid \n",
+      "h0s=ntt*h0#Change in enthalpy of process in kJ/kg\n",
+      "P0=((h0s*1000)/100)#Change in pressure in bar\n",
+      "P02=P0+P01#Total outlet pressure of fliud in bar\n",
+      "P2=(P02/P01)#Total pressure ratio of fliud\n",
+      "\n",
+      "#output\n",
+      "print '''(a)The exit total temperature of fliud is %3.2f K\n",
+      "(b)The total pressure ratio if:\n",
+      "(1)The fliud is air is %3.3f\n",
+      "(2)The fliud is liquid water is %3.0i'''%(T02,P1,P2)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The exit total temperature of fliud is 308.97 K\n",
+        "(b)The total pressure ratio if:\n",
+        "(1)The fliud is air is 1.053\n",
+        "(2)The fliud is liquid water is  46\n"
+       ]
+      }
+     ],
+     "prompt_number": 3
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 1.4 Page 22"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "W=100#Output power developed in kW\n",
+      "Q=0.1#Flow through device in m**3/s\n",
+      "d=800#Density of oil in kg/m**3\n",
+      "ntt=0.75#Total-to-total efficiency\n",
+      "C1=3#inlet flow velocity of oil in m/s\n",
+      "C2=10#outlet flow velocity of oil in m/s\n",
+      "\n",
+      "#calculations\n",
+      "m=d*Q#Mass flow rate of oil in kg/s\n",
+      "h0=-(W/m)#Change in total enthalpy in kJ/kg\n",
+      "h0s=(h0/ntt)#Isentropic change in total enthalpy in kJ/kg\n",
+      "P0=((d*h0s)*(1/100))#Change in total pressure of oil in bar\n",
+      "P=P0-((d/(2000*100))*(C2**2-C1**2))#Change in static pressure in bar\n",
+      "\n",
+      "#output\n",
+      "print '''The change in total pressure of oil is %3.1f bar\n",
+      "The change in static presure is %3.1f bar'''%(P0,P)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "The change in total pressure of oil is -13.3 bar\n",
+        "The change in static presure is -13.7 bar\n"
+       ]
+      }
+     ],
+     "prompt_number": 4
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 1.5 Page 22"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "N=4#Number of stages in turbine handling\n",
+      "P=0.4#Stagnation presure ratio between exit and inlet of each stage\n",
+      "ns1=0.86#Stage efficiency of first and second stages\n",
+      "ns2=0.84#Stage efficiency of third and fourth stages\n",
+      "r=1.4#ratio of specific heats for air\n",
+      "\n",
+      "#calculations\n",
+      "u=1-(P)**((r-1)/r)#constant\n",
+      "T03=(1-(u*ns1))**2#Temperature after the end of first two stages in (K*Cp*T01) where Cp is specific at heat at constant pressure in kJ/kg.K and T01 is initial temperature at entry of stage 1 in K\n",
+      "W12=u*(1+(1-(u*ns1)))*ns1#Actual work output from first two stages in (kW*Cp*T01)\n",
+      "W34=T03*u*(1+(1-(u*ns2)))*ns2#Actual work output from last two stages in (kW*Cp*T01)\n",
+      "W=(W12+W34)#Total actual work output from turbine in (kW*Cp*T01)\n",
+      "Ws=1-(1-u)**N#Total isentropic work due to single stage compressor in (kW*Cp*T01)\n",
+      "n=(W/Ws)#Overall turbine efficiency\n",
+      "\n",
+      "#output\n",
+      "print 'the overall efficiency of the turbine is %.1f %%'%(n*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "the overall efficiency of the turbine is 89.6 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 5
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 1.6 Page 24"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "\n",
+      "from __future__ import division\n",
+      "from math import log10\n",
+      "#input data\n",
+      "P=1400#Pressure developed by compressor in mm W.G\n",
+      "P1=1.01#Initial pressure of air in bar\n",
+      "T1=305#Initial temperature of air in K\n",
+      "T2=320#Final temperature of air in K\n",
+      "P=1400*9.81*10**-5#Pressure developed by compressor in bar\n",
+      "r=1.4#ratio of specific heats for air\n",
+      "\n",
+      "#calculations\n",
+      "P2=P1+P#Final pressure of air in bar\n",
+      "T2s=T1*(P2/P1)**((r-1)/r)#Isentropic temperature at exit in K\n",
+      "nc=((T2s-T1)/(T2-T1))#compressor efficiency\n",
+      "np=((r-1)/r)*((log10(P2/P1))/(log10(T2/T1)))#Infinitesimal stage efficiency\n",
+      "\n",
+      "#output\n",
+      "print '''(a)The compressor efficiency is %0.2f %%\n",
+      "(b)The infinitesimal stage efficiency is %0.2f %%'''%(nc*100,np*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The compressor efficiency is 75.43 %\n",
+        "(b)The infinitesimal stage efficiency is 75.88 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 6
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 1.7 Page 24"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "P1=1.01#Input pressure to compressor in bar\n",
+      "T1=305#Input temperature to compressor in K\n",
+      "P2=3#Output pressure from compressor in bar\n",
+      "r=1.4#ratio of specific heats for air\n",
+      "nc=0.75#compressor efficiency\n",
+      "\n",
+      "#calculations\n",
+      "T2s=T1*(P2/P1)**((r-1)/r)#Isentropic output temperature from compressor in K\n",
+      "T2=T1+((T2s-T1)/nc)#Actual output temperature from compressor in K\n",
+      "np=((r-1)/r)*((log10(P2/P1))/(log10(T2/T1)))#Infinitesimal efficiency of compressor\n",
+      "\n",
+      "#output\n",
+      "print 'The infinitesimal efficiency of the compressor is %0.1f %%'%(np*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "The infinitesimal efficiency of the compressor is 78.5 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 7
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 1.8 Page 25"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "P=2.2#Pressure ratio across a gas turbine\n",
+      "n=0.88#Efficiency of a gas turbine\n",
+      "T1=1500#Inlet temperature of the gas in K\n",
+      "r=1.4#ratio of specific heats for air\n",
+      "\n",
+      "#calculations\n",
+      "T2s=T1*(1/P)**((r-1)/r)#Isentropic output temperature from gas turbine in K\n",
+      "T2=T1-(n*(T1-T2s))#actual output temperature from gas turbine in K\n",
+      "np=(r/(r-1))*((log10(T1/T2))/(log10(P)))#Polytropic efficiency of the turbine\n",
+      "\n",
+      "\n",
+      "#output\n",
+      "print 'The polytropic efficiency of the turbine is %0.1f %%'%(np*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "The polytropic efficiency of the turbine is 86.7 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 8
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 1.9 Page 26"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "# input data\n",
+      "P=1.3#Pressure ratio of stages\n",
+      "N=8#Number of stages\n",
+      "m =45#The flow rate through compressor in kg/s\n",
+      "nc=0.8#Overall efficiency of the compressor\n",
+      "P1=1#Initial pressure of the air at entry in bar\n",
+      "T1=308#Initial temperature of the air at entry in K\n",
+      "r=1.4#ratio of specific heats for air\n",
+      "\n",
+      "#calculations\n",
+      "PN=(P)**8#Overall pressure ratio of all 8 stages\n",
+      "TN=PN**((r-1)/r)#Overall temperature ratio of all 8 stages\n",
+      "TN1s=TN*T1#Ideal exit temperature in K\n",
+      "TN1=((TN1s-T1)/nc)+T1#Actual exit temperature in K\n",
+      "PN1=PN*P1#Actual exit pressure in bar\n",
+      "np=((r-1)/r)*((log10(PN1/P1))/(log10(TN1/T1)))#Polytropic efficiency of the cycle\n",
+      "ns=((((P)**((r-1)/r))-1)/(((P)**((r-1)/(r*np)))-1))#The stage efficiency of the cycle\n",
+      "\n",
+      "#output\n",
+      "print '''(a)The state of air at compressor exit are-\n",
+      "(1)actual temperature is %3.1f K\n",
+      "(2)actual pressure is %3.2f bar\n",
+      "(b)The polytropic efficiency of the cycle is %0.f %%\n",
+      "(c)The stage efficiency of the cycle is %0.2f %%'''%(TN1,PN1,np*100,ns*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The state of air at compressor exit are-\n",
+        "(1)actual temperature is 624.3 K\n",
+        "(2)actual pressure is 8.16 bar\n",
+        "(b)The polytropic efficiency of the cycle is 85 %\n",
+        "(c)The stage efficiency of the cycle is 84.31 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 9
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex - 1.10 Page 27"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import log10\n",
+      "#input data\n",
+      "P=11#Overall pressure ratio in three stages of a gas turbine\n",
+      "nt=0.88#Overall efficiency in three stages of a gas turbine\n",
+      "T1=1500#Temperature at inlet of a gas turbine in K\n",
+      "r=1.4#ratio of specific heats for air\n",
+      "\n",
+      "#calculations\n",
+      "T0=nt*T1*(1-(1/P)**((r-1)/r))#Overall change in temperature in all stages in K\n",
+      "TN1=T1-T0#Temperature at final stage of a gas turbine in K\n",
+      "np=((r/(r-1))*log10(T1/TN1))/(log10(P))#Overall polytropic efficiency of the gas turbine\n",
+      "Ts=T0/3#Individual stage change in temperature in K\n",
+      "T2=T1-Ts#Exit temperature at the end of first stage in K\n",
+      "P1=(T1/T2)**(r/(np*(r-1)))#Pressure ratio at first stage of gas turbine \n",
+      "ns1=((1-(1/P1)**((np*(r-1))/r))/(1-(1/P1)**((r-1)/r)))#Stage efficiency of first stage \n",
+      "T3=T2-Ts#Exit temperature at the end of second stage in K\n",
+      "P2=(T2/T3)**(r/(np*(r-1)))#Pressure ratio at second stage of gas turbine\n",
+      "ns2=((1-(1/P2)**((np*(r-1))/r))/(1-(1/P2)**((r-1)/r)))#Stage efficiency of second stage\n",
+      "T4=T3-Ts#Exit temperature at the end of third stage in K\n",
+      "P3=(T3/T4)**(r/(np*(r-1)))#Pressure ratio at the third stage of gas turbine\n",
+      "ns3=((1-(1/P3)**((np*(r-1))/r))/(1-(1/P3)**((r-1)/r)))#Stage efficiency of third stage\n",
+      "\n",
+      "#output\n",
+      "print '''(a)The values for first stage are -\n",
+      "(1)Pressure ratio is %3.2f\n",
+      "(2)stage efficiency is %0.2f %%\n",
+      "(b)The values of second stage are -\n",
+      "(1)Pressure ratio is %3.3f\n",
+      "(2)Stage efficiency is %0.1f %%\n",
+      "(c)The values of third stage are -\n",
+      "(1)Pressure ratio is %3.2f\n",
+      "(2)Stage efficiency is %0.2f'''%(P1,ns1*100,P2,ns2*100,P3,ns3*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The values for first stage are -\n",
+        "(1)Pressure ratio is 1.93\n",
+        "(2)stage efficiency is 84.96 %\n",
+        "(b)The values of second stage are -\n",
+        "(1)Pressure ratio is 2.182\n",
+        "(2)Stage efficiency is 85.2 %\n",
+        "(c)The values of third stage are -\n",
+        "(1)Pressure ratio is 2.61\n",
+        "(2)Stage efficiency is 85.52\n"
+       ]
+      }
+     ],
+     "prompt_number": 10
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 1.11 Page 29  "
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "N=4#Number of stages in compressor\n",
+      "m=45#mass flow rate of air delivered by compressor in kg/s\n",
+      "P1=1.2#Pressure ratio at first stage\n",
+      "ns=0.65#Stage efficiency of first stage\n",
+      "r=1.4#ratio of specific heats for air\n",
+      "Cp=1.005#specific at heat at constant pressure in kJ/kg.K\n",
+      "T1=293#Temperature of air at inlet in K\n",
+      "\n",
+      "#calculations\n",
+      "P=(P1)**N#Overall pressure in all 4 stages\n",
+      "np=((r-1)/r)*((log10(P1))/(log10((((P1**((r-1)/r))-1)/ns)+1)))#Polytropic efficiency of the cycle\n",
+      "nc=(((P1**(N*((r-1)/r)))-1)/((P1**(N*((r-1)/(r*np))))-1))#Overall efficiency of the cycle\n",
+      "TN1=T1*((P1**(N))**((r-1)/(r*np)))#Final temperature at the exit of the compressor at final stage in K\n",
+      "W=m*Cp*(TN1-T1)#Power required to drive the compressor in kW\n",
+      "\n",
+      "#output\n",
+      "\n",
+      "print '''(a)The overall pressure ratio of the process is %3.1f\n",
+      "(b)The overall efficiency of the process is %0.2f %%\n",
+      "(c)The power required to drive the compressor is %3.2f kW'''%(P,nc*100,W)\n",
+      "# the answer in the textbook is not correct."
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The overall pressure ratio of the process is 2.1\n",
+        "(b)The overall efficiency of the process is 62.29 %\n",
+        "(c)The power required to drive the compressor is 4928.55 kW\n"
+       ]
+      }
+     ],
+     "prompt_number": 11
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 1.12 Page 31  "
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "P0=0.2*9.81*(10**3)*(10**-5)#Total increase in pressure in bar\n",
+      "P01=1.04#Total inlet pressure of air in bar\n",
+      "T01=291#Total inlet temperature of air in K\n",
+      "ntt=0.72#Total-to-total efficiency of the process\n",
+      "r=1.4#ratio of specific heats for air\n",
+      "Cp=1.005#specific at heat at constant pressure in kJ/kg.K\n",
+      "\n",
+      "#calculations\n",
+      "P2=P0+P01#The total exit pressure in bar\n",
+      "T02=((((P2/P01)**((r-1)/r)-1)*T01)/ntt)+T01#Total temperature at the outlet in K\n",
+      "h0=Cp*(T02-T01)#Actual change in total enthalpy in kJ/kg\n",
+      "h0s=h0*ntt#Isentropic change in total enthalpy in kJ/kg\n",
+      "\n",
+      "#output\n",
+      "print '''(a)The total exit pressure is %3.4f bar\n",
+      "and the total exit temperature is %3.2f K\n",
+      "(b)The actual change in total enthalpy is %3.3f kJ/kg\n",
+      "and the isentropic change in total enthalpy is %3.3f kJ/kg'''%(P2,T02,h0,h0s)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The total exit pressure is 1.0596 bar\n",
+        "and the total exit temperature is 293.16 K\n",
+        "(b)The actual change in total enthalpy is 2.175 kJ/kg\n",
+        "and the isentropic change in total enthalpy is 1.566 kJ/kg\n"
+       ]
+      }
+     ],
+     "prompt_number": 12
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 1.13 Page 31"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "P=5#Pressure ratio in the process\n",
+      "ntt=0.8#Total-to-total efficiency of the process\n",
+      "m=5#Air flow rate through turbine in kg/s\n",
+      "W=500#Total power output from the turbine in kW\n",
+      "r=1.4#ratio of specific heats for air\n",
+      "Cp=1.005*10**3#specific at heat at constant pressure in J/kg.K\n",
+      "C2=100#Flow velocity of air in m/s\n",
+      "\n",
+      "#calculations\n",
+      "T=(W*10**3)/(m*Cp)#Total change in temperature in the process in K\n",
+      "T02s=(1/P)**((r-1)/r)#Isentropic temperature at the outlet from turvine in (K*T01)\n",
+      "T01=(T/ntt)*(1/(1-0.631))#Inlet total temperature in K\n",
+      "T02=T01-T#Actual exit total temperature in K\n",
+      "T2=T02-((C2**2)/(2*Cp))#Actual exit static temperature in K\n",
+      "T02s1=T02s*T01#Isentropic temperature at the outlet from turbine in K\n",
+      "T2s=T02s1-((C2**2)/(2*Cp))#Actual isentropic temperature in K\n",
+      "nts=(T/(T01-T2s))#Total-to-static efficiency\n",
+      "\n",
+      "#output\n",
+      "print '''(a)The inlet total temperature is %i K\n",
+      "(b)The actual exit total temperature is %3.1f K\n",
+      "(c)The actual exit static temperature is %3.1f K\n",
+      "(d)The total-to-static efficiency is %0.2f  %%'''%(T01,T02,T2,nts*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The inlet total temperature is 337 K\n",
+        "(b)The actual exit total temperature is 237.6 K\n",
+        "(c)The actual exit static temperature is 232.6 K\n",
+        "(d)The total-to-static efficiency is 77.00  %\n"
+       ]
+      }
+     ],
+     "prompt_number": 13
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 1.14 Page 33  "
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import log\n",
+      "#input data\n",
+      "N=3#Number of stages in turbine\n",
+      "P=2#Pressure ratio of each stage\n",
+      "ns=0.75#Stage efficiency of each stage\n",
+      "T1=873#Initial temperature of air in K\n",
+      "m=25#Flow rate of air in kg/s\n",
+      "r=1.4#ratio of specific heats for air\n",
+      "Cp=1.005#specific at heat at constant pressure in J/kg.K\n",
+      "\n",
+      "#calculations\n",
+      "np=(r/(r-1))*((log(1-(ns*(1-(1/P)**((r-1)/r)))))/(log(1/P)))#Polytropic efficiency of the process\n",
+      "nt=((1-(1/P)**(N*np*((r-1)/r)))/(1-(1/P)**(N*((r-1)/r))))#Overall efficiency of the turbine\n",
+      "W=m*Cp*T1*(1-(1/P)**(N*np*((r-1)/r)))#Power developed by the turbine in kW\n",
+      "RF=nt/ns#Reheat factor of the process\n",
+      "\n",
+      "#output\n",
+      "print '''(a)The overall efficiency of the turbine is %0.2f %%\n",
+      "(b)The power developed by the turbine is %i kW\n",
+      "(c)The reheat factor of the process is %3.2f'''%(nt*100,W,RF)\n",
+      "\n",
+      "#comments\n",
+      "# the answer in the textbook is not correct."
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The overall efficiency of the turbine is 78.63 %\n",
+        "(b)The power developed by the turbine is 7725 kW\n",
+        "(c)The reheat factor of the process is 1.05\n"
+       ]
+      }
+     ],
+     "prompt_number": 14
+    }
+   ],
+   "metadata": {}
+  }
+ ]
+}
\ No newline at end of file
diff --git a/Turbomachines_by_A._V._Arasu/Ch2.ipynb b/Turbomachines_by_A._V._Arasu/Ch2.ipynb
new file mode 100644
index 00000000..380bdf26
--- /dev/null
+++ b/Turbomachines_by_A._V._Arasu/Ch2.ipynb
@@ -0,0 +1,435 @@
+{
+ "metadata": {
+  "name": "",
+  "signature": "sha256:f90ad248f5346a845ec01efdf3c2941322625ecb2d8d238ed549e14c9d9de3bb"
+ },
+ "nbformat": 3,
+ "nbformat_minor": 0,
+ "worksheets": [
+  {
+   "cells": [
+    {
+     "cell_type": "heading",
+     "level": 1,
+     "metadata": {},
+     "source": [
+      "Chapter 2 - Blade Theory"
+     ]
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 2.1 page 53"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "c =2.25#Chord length of an aerofoil in m\n",
+      "l=13.5#Span of the aerofoil in m\n",
+      "C=125#Velocity of the aerofoil in m/s\n",
+      "Cl=0.465#Lift coefficient\n",
+      "Cd=0.022#Drag coefficient\n",
+      "d=1.25#Density of the air in kg/m**3\n",
+      "\n",
+      "#calculations\n",
+      "A=c*l#Area of cross section of the aerofoil in m**2\n",
+      "W=Cl*d*((C**2)/2)*A*10**-3#Weight carried by the wings of aerofoil in kN\n",
+      "D=Cd*d*((C**2)/2)*A#Drag force on the wings of aerofoil in N\n",
+      "P=D*C*10**-3#Power required to the drive the aerofoil in kW\n",
+      "\n",
+      "#output\n",
+      "print '''(a)Weight carrried by the wings is %3.2f kN\n",
+      "(b)Drag force on the wings of aerofoil is %3.2f N\n",
+      "(c)Power required to drive the aerofoil is %3.3f kW'''%(W,D,P)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Weight carrried by the wings is 137.92 kN\n",
+        "(b)Drag force on the wings of aerofoil is 6525.46 N\n",
+        "(c)Power required to drive the aerofoil is 815.683 kW\n"
+       ]
+      }
+     ],
+     "prompt_number": 1
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 2.2 page 53"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from __future__ import division\n",
+      "#input data\n",
+      "W=980#The weight of the object being dropped by parachute in N\n",
+      "C=5#The maximum terminal velocity of dropping in m/s\n",
+      "d=1.22#The density of the air in kg/m**3\n",
+      "Cd=1.3#The drag coefficient of the parachute\n",
+      "\n",
+      "#calculations\n",
+      "A=W/(Cd*d*((C**2)/2))#The area of cross section in m**2\n",
+      "D=((A*4)/(3.14))**(1/2)#Diameter of the parachute in m\n",
+      "\n",
+      "#output\n",
+      "print 'The required diameter of the parachute is %3.2f m'%(D)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "The required diameter of the parachute is 7.94 m\n"
+       ]
+      }
+     ],
+     "prompt_number": 2
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 2.3 page 54"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "A=10*1.2#Area of the airplane wing in m**2\n",
+      "C=((240*10**3)/3600)#Velocity of the wing in m/s\n",
+      "F=20#Total aerodynamic force acting on the wing in kN\n",
+      "LD=10#Lift-drag ratio\n",
+      "d=1.2#Density of the air in kg/m**3\n",
+      "\n",
+      "#calculations\n",
+      "L=(F)/(1.01)**(1/2)#The weight that the plane can carry in kN\n",
+      "Cl=(L*10**3)/(d*A*((C**2)/2))#Coefficient of the lift\n",
+      "\n",
+      "#output\n",
+      "print '(1)The coefficient of lift is %3.3f\\n(2)The total weight the palne can carry is %3.1f kN'%(Cl,L)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(1)The coefficient of lift is 0.622\n",
+        "(2)The total weight the palne can carry is 19.9 kN\n"
+       ]
+      }
+     ],
+     "prompt_number": 3
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 2.4 page 54"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "m=25#Mass flow rate of the air in kg/s\n",
+      "d=1.1#Density of the air in kg/m**3\n",
+      "Ca=157#Axial flow velocity of the air in m/s\n",
+      "N=150#Rotational speed of the air in rev/s\n",
+      "U=200#Mean blade speed in m/s\n",
+      "lc=3#Rotor blade aspect ratio \n",
+      "sc=0.8#Pitch chord ratio\n",
+      "\n",
+      "#calculations\n",
+      "rm=(U)/(2*3.145*N)#Mean radius of the blades in m\n",
+      "A=(m)/(d*Ca)#The annulus area of flow in m**2\n",
+      "l=(A)/(2*3.1*rm)#The blade height in m\n",
+      "C=l/lc#The chord of the blades in m\n",
+      "S=sc*C#The blade pitch in m\n",
+      "n=(2*3.141*rm)/(S)#Number of blades \n",
+      "\n",
+      "#output\n",
+      "\n",
+      "print '''(a)The mean radius of the blades is %3.3f m\n",
+      "(b)The blade height is %3.2f m\\n(c) (1)The pitch of the blades is %3.4f m\n",
+      "(2)The chord of the blades is %3.3f m\\n(d)The number of the blades are %3.f'''%(rm,l,S,C,n)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The mean radius of the blades is 0.212 m\n",
+        "(b)The blade height is 0.11 m\n",
+        "(c) (1)The pitch of the blades is 0.0294 m\n",
+        "(2)The chord of the blades is 0.037 m\n",
+        "(d)The number of the blades are  45\n"
+       ]
+      }
+     ],
+     "prompt_number": 4
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 2.5 page 56"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "sc=0.8#Pitch-chord ratio of compressor blade\n",
+      "b1=45#Relative air angle at inlet in degree\n",
+      "b2=15#Relative air angle at oulet in degree\n",
+      "a1=b1#Cascade air angle at inlet in degree\n",
+      "a2=b2#Cascade air angle at outlet in degree\n",
+      "\n",
+      "#calculations \n",
+      "en=a1-a2#Nominal deflection angle of the blade in degree\n",
+      "m=((0.23*(1)**2))+(0.1*a2/50)#An emperical constant for a circular arc camber where (2*a/c)=1\n",
+      "t=(a1-a2)/(1-0.233)#Blade camber angle in degree\n",
+      "d=(m*(sc)**(1/2))*t#The deviation angle of the blade in terms of (degree*t)\n",
+      "ps=a1-(t/2)#The blade stagger for a given circular arc cascade in degree\n",
+      "\n",
+      "#output\n",
+      "print '''(a)The nominal deflection angle is %i degree\n",
+      "(b)The blade camber angle is %3.2f degree\n",
+      "(c)The deviation angle is %3.2f degree\n",
+      "(d)The blade stagger is %3.2f degree'''%(en,t,d,ps)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The nominal deflection angle is 30 degree\n",
+        "(b)The blade camber angle is 39.11 degree\n",
+        "(c)The deviation angle is 9.10 degree\n",
+        "(d)The blade stagger is 25.44 degree\n"
+       ]
+      }
+     ],
+     "prompt_number": 5
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 2.6 page 57"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import atan, degrees, tan\n",
+      "#input data\n",
+      "t=25#The camber angle of aero foil blades in degree\n",
+      "ps=30#The blade stagger angle in degree\n",
+      "sc=1#The pitch-chord ratio of the blades\n",
+      "In=5#The nominal value of incidence in degree\n",
+      "\n",
+      "#calculations\n",
+      "a1=ps+(t/2)#The cascade blade angle at inlet in degree\n",
+      "a2=a1-t#The cascade blade angle at outlet in degree\n",
+      "a1n=In+a1#The nominal entry air angle in degree\n",
+      "a2n=degrees(atan((tan(a1n))-(1.55/(1.0+(1.5*sc)))))#The nominal exit air angle in degree\n",
+      "\n",
+      "#output\n",
+      "print '''(1)The cascade blade angles at -\n",
+      "(a)inlet is %3.1f degree\n",
+      "(b)exit is %3.1f degree\n",
+      "(2)The nominal air angles at -\n",
+      "(a)inlet is %3.1f degree\n",
+      "(b)exit is %3.2f degree'''%(a1,a2,a1n,a2n)\n",
+      "# the answer in the textbook is not correct."
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(1)The cascade blade angles at -\n",
+        "(a)inlet is 42.5 degree\n",
+        "(b)exit is 17.5 degree\n",
+        "(2)The nominal air angles at -\n",
+        "(a)inlet is 47.5 degree\n",
+        "(b)exit is -12.69 degree\n"
+       ]
+      }
+     ],
+     "prompt_number": 6
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 2.7 page 58"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import atan, cos, tan, pi\n",
+      "#input data\n",
+      "C1=75#Velocity of air entry in m/s\n",
+      "a1=48#Air angle at entry in degree\n",
+      "a2=25#Air angle at exit in degree\n",
+      "cs=0.91#The chord-pitch ratio \n",
+      "P0m=(11*9.81*10**3)/10**3#The stagnation pressure loss in N/m**2\n",
+      "d=1.25#The density of the sair in kg/m**3\n",
+      "\n",
+      "#calculations\n",
+      "Cp=(P0m/(0.5*d*C1**2))#The pressure loss coefficient \n",
+      "am=degrees(atan((tan(a1)+tan(a2))/2))#The mean air angle in degree\n",
+      "Cd=2*(1/cs)*(P0m/(d*C1**2))*((cos(pi/180*am))**3/(cos(pi/180*a1))**2)#The drag coefficient \n",
+      "Cl=(2*(1/cs)*cos(pi/180*am)*(tan(pi/180*a1)-tan(pi/180*a2)))-(Cd*tan(pi/180*am))#THe lift coefficient\n",
+      "\n",
+      "#output\n",
+      "print '''(a)The pressure loss coefficient is %3.4f\n",
+      "(b)The drag coefficient is %3.4f\\n(c)The lift coefficient is %3.3f'''%(Cp,Cd,Cl)\n",
+      "# the answer in the textbook is not correct."
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The pressure loss coefficient is 0.0307\n",
+        "(b)The drag coefficient is 0.0518\n",
+        "(c)The lift coefficient is 1.222\n"
+       ]
+      }
+     ],
+     "prompt_number": 7
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 2.8 page 59"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "a1=40#The cascade air angle at entry in degree\n",
+      "a2=65#The cascade air angle at exit in degree\n",
+      "C1=100#Air entry velocity in m/s\n",
+      "d=1.25#The density of the air in kg/m**3\n",
+      "sc=0.91#The pitch-chord ratio of the cascade\n",
+      "P0m=(17.5*9.81*10**3)/10**3#The average loss in stagnation pressure across cascade in N/m**2\n",
+      "\n",
+      "#calculations\n",
+      "Cp=(P0m/(0.5*d*C1**2))#The pressure loss coefficient in the cascade\n",
+      "am=atan((tan(a2)-tan(a1))/2)#The mean air angle in degree\n",
+      "Cd=2*(sc)*(P0m/(d*C1**2))*((cos(pi/180*am))**3/(cos(pi/180*a2))**2)#The drag coefficient \n",
+      "Cl=(2*(sc)*cos(pi/180*am)*(tan(pi/180*a1)+tan(pi/180*a2)))+(Cd*tan(pi/180*am))#THe lift coefficient\n",
+      "\n",
+      "#output\n",
+      "print '(a)The pressure loss coefficient is %3.4f\\n(b)The drag coefficient is %3.4f\\n(c)The lift coefficient is %3.3f'%(Cp,Cd,Cl)\n",
+      "# the answer in the textbook is not correct."
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The pressure loss coefficient is 0.0275\n",
+        "(b)The drag coefficient is 0.1399\n",
+        "(c)The lift coefficient is 5.430\n"
+       ]
+      }
+     ],
+     "prompt_number": 8
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 2.9 page 60"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "W=30000#The weight of the jet plane in N\n",
+      "A=20#The area of the wing in m**2\n",
+      "C=250*5/18#The speed of the jet plane in m/s\n",
+      "P=750#The power delivered by the engine in kW\n",
+      "d=1.21#Density of the air in kg/m**3\n",
+      "\n",
+      "#calculations\n",
+      "L=W#The lift force on the plane is equal to the weight of the plane in N\n",
+      "Pd=0.65*P#The power required to overcome the drag resistance in kW\n",
+      "D=(Pd/C)*10**3#The drag force on the wing in N\n",
+      "Cd=D/(0.5*d*A*C**2)#The coefficient of drag for the wing \n",
+      "Cl=L/(0.5*d*A*C**2)#The coefficient of lift for the wing \n",
+      "\n",
+      "#output\n",
+      "print '(a)The coefficient of lift on the wing is %3.3f\\n(b)The coefficient of drag on the wing is %3.3f'%(Cl,Cd)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The coefficient of lift on the wing is 0.514\n",
+        "(b)The coefficient of drag on the wing is 0.120\n"
+       ]
+      }
+     ],
+     "prompt_number": 9
+    }
+   ],
+   "metadata": {}
+  }
+ ]
+}
\ No newline at end of file
diff --git a/Turbomachines_by_A._V._Arasu/Ch3.ipynb b/Turbomachines_by_A._V._Arasu/Ch3.ipynb
new file mode 100644
index 00000000..d1cafb38
--- /dev/null
+++ b/Turbomachines_by_A._V._Arasu/Ch3.ipynb
@@ -0,0 +1,844 @@
+{
+ "metadata": {
+  "name": "",
+  "signature": "sha256:dc07aa3042daa4cf3235ebcee99afeac70f8ff9726da7fd96f3108e76e2b9625"
+ },
+ "nbformat": 3,
+ "nbformat_minor": 0,
+ "worksheets": [
+  {
+   "cells": [
+    {
+     "cell_type": "heading",
+     "level": 1,
+     "metadata": {},
+     "source": [
+      "Chapter 3 - Centrifugal Compressors & Fans"
+     ]
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 3.1 Page 93"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from __future__ import division\n",
+      "#input data\n",
+      "m=10#The mass flow rate of air into compressor in kg/s\n",
+      "P1=1#The ambient air pressure in compressor in bar\n",
+      "T1=293#The ambient air temperature in compressor in K\n",
+      "N=20000#The running speed of the compressor in rpm\n",
+      "nc=0.8#The isentropic efficiency of the compressor\n",
+      "P02=4.5#The total exit pressure from the compressor in bar\n",
+      "C1=150#The air entry velocity into the impeller eye in m/s\n",
+      "Cx1=0#The pre whirl speed in m/s\n",
+      "WS=0.95#The ratio of whirl speed to tip speed\n",
+      "Cp=1005#The specific heat of air at constant pressure in J/kg.K \n",
+      "R=287#The universal gas constant in J/kg.K\n",
+      "Dh=0.15#The eye internal diamater in m\n",
+      "r=1.4#Ratio of specific heats of air \n",
+      "d=1.189#The density of the air in kg/m**3\n",
+      "\n",
+      "#calculations\n",
+      "T01=T1+((C1**2)/(2*Cp))#The stagnation temperature at inlet in K\n",
+      "P01=P1*(T01/T1)**(r/(r-1))#The stagnation pressure at inlet in bar\n",
+      "T02s=(T01)*(P02/P01)**((r-1)/r)#The temperature after isentropic compression from P01 to P02 in K\n",
+      "T=(T02s-T01)/nc#The actual rise in total temperature in K\n",
+      "W=Cp*(10**-3)*(T)#The work done per unit mass in kJ/kg\n",
+      "U2=((W*(10**3))/(WS))**(1/2)#The impeller tip speed in m/s\n",
+      "Dt=(U2*60)/(3.1415*N)#The impeller tip diameter in m\n",
+      "P=m*W#Power required to drive the compressor in kW\n",
+      "d1=((P1*10**5)/(R*T1))#The density of the air entry in kg/m**3\n",
+      "De=(((4*m)/(d*C1*3.14))+(Dh**2))**(1/2)#The eye external diameter in m\n",
+      "\n",
+      "#output\n",
+      "print '(a)The actual rise in total temperature of the compressor is %3.1f K\\n(b)\\n      (1)The impeller tip speed is %3.2f m/s\\n      (2)The impeller tip diameter is %3.2f m\\n(c)The power required to drive the compressor is %3.1f kW\\n(d)The eye external diameter is %0.1f cm'%(T,U2,Dt,P,De*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The actual rise in total temperature of the compressor is 182.6 K\n",
+        "(b)\n",
+        "      (1)The impeller tip speed is 439.55 m/s\n",
+        "      (2)The impeller tip diameter is 0.42 m\n",
+        "(c)The power required to drive the compressor is 1835.4 kW\n",
+        "(d)The eye external diameter is 30.6 cm\n"
+       ]
+      }
+     ],
+     "prompt_number": 1
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 3.2 Page 95"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import degrees, atan\n",
+      "#input data\n",
+      "Q1=20#Discharge of air to the centrifugal compressor in m**3/s\n",
+      "V1=Q1#Volume of rate is equal to the discharge in m**3/s\n",
+      "P1=1#Initial pressure of the air to the centrifugal compressor in bar\n",
+      "T1=288#Initial temperature of the air to the centrifugal compressor in K\n",
+      "P=1.5#The pressure ratio of compression in centrifugal compressor\n",
+      "C1=60#The velocity of flow of air at inlet in m/s\n",
+      "Cr2=C1#The radial velocity of flow of air at outlet in m/s\n",
+      "Dh=0.6#The inlet impeller diameter in m\n",
+      "Dt=1.2#The outlet impeller diameter in m\n",
+      "N=5000#The speed of rotation of centrifugal compressor in rpm\n",
+      "n=1.5#polytropic index constant in the given law PV**n\n",
+      "Cp=1005#The specific heat of air at constant pressure in J/kg.K \n",
+      "\n",
+      "#calculations\n",
+      "U1=(3.14*Dh*N)/60#Peripheral velocity of impeller at inlet in m/s\n",
+      "b11=degrees(atan(C1/U1))#The blade angle at impeller inlet in degree\n",
+      "U2=(3.14*Dt*N)/60#Peripheral velocity of impeller top at outlet in m/s\n",
+      "T2=T1*(P)**((n-1)/n)#Final temperature of the air to the centrifugal compressor in K\n",
+      "Cx2=((Cp*(T2-T1))/U2)#The whirl component of absolute velocity in m/s\n",
+      "Wx2=U2-Cx2#The exit relative velocity in m/s\n",
+      "a2=degrees(atan(Cr2/Cx2))#The blade angle at inlet to casing in degree\n",
+      "b22=degrees(atan(Cr2/Wx2))#The blade angle at impeller outlet in degree\n",
+      "b1=Q1/(2*3.14*(Dh/2)*C1)#The breadth of impeller blade at inlet in m \n",
+      "V2=(P1*V1*T2)/(T1*P*P1)#Volume flow rate of air at exit in m**3/s\n",
+      "Q2=V2#Volume flow rate is equal to discharge in m**3/s\n",
+      "b2=Q2/(2*3.14*(Dt/2)*Cr2)#The breadth of impeller blade at outlet in m\n",
+      "\n",
+      "#output\n",
+      "print '(a)The blade and flow angles\\n   (1)The blade angle at impeller inlet is %3.1f degree\\n   (2)The blade angle at inlet to casing is %3.1f degree\\n   (3)The blade angle at impeller outlet is %3.2f degree\\n(b)Breadth of the impeller blade at inlet and outlet\\n   (1)The breadth of impeller blade at inlet is %3.3f m\\n   (2)The Volume flow rate of air at exit is %3.2f m**3/s\\n   (3)The breadth of impeller blade at outlet is %3.4f m'%(b11,a2,b22,b1,V2,b2)\n",
+      "\n",
+      "\n",
+      "#comments\n",
+      "#error in the first review is not printing the value of V2 which is corrected"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The blade and flow angles\n",
+        "   (1)The blade angle at impeller inlet is 20.9 degree\n",
+        "   (2)The blade angle at inlet to casing is 24.2 degree\n",
+        "   (3)The blade angle at impeller outlet is 18.38 degree\n",
+        "(b)Breadth of the impeller blade at inlet and outlet\n",
+        "   (1)The breadth of impeller blade at inlet is 0.177 m\n",
+        "   (2)The Volume flow rate of air at exit is 15.26 m**3/s\n",
+        "   (3)The breadth of impeller blade at outlet is 0.0675 m\n"
+       ]
+      }
+     ],
+     "prompt_number": 2
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 3.3 Page 97"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "m=14#The mass flow rate of air delivered to centrifugal compressor in kg/s\n",
+      "P01=1#The inlet stagnation pressure in bar\n",
+      "T01=288#The inlet stagnation temperature in K\n",
+      "P=4#The stagnation pressure ratio\n",
+      "N=200#The speed of centrifygal compressor in rps\n",
+      "ss=0.9#The slip factor\n",
+      "ps=1.04#The power input factor\n",
+      "ntt=0.8#The overall isentropic efficiency\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",
+      "pp=ss*ps*ntt#The pressure coefficient\n",
+      "U2=((Cp*T01*((P**((r-1)/r))-1))/pp)**(1/2)#Peripheral velocity of impeller top at outlet in m/s\n",
+      "D2=U2/(3.14*N)#The overall diameter of the impeller in m\n",
+      "\n",
+      "#output\n",
+      "print 'The overall diameter of the impeller is %.f cm'%(D2*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "The overall diameter of the impeller is 69 cm\n"
+       ]
+      }
+     ],
+     "prompt_number": 3
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 3.4 Page 98"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import cos, pi, tan\n",
+      "#input data\n",
+      "D1=0.457#Impeller diameter at inlet in m\n",
+      "D2=0.762#Impeller diameter at exit in m\n",
+      "Cr2=53.4#Radial component of velocity at impeller exit in m/s\n",
+      "ss=0.9#Slip factor\n",
+      "N=11000#Impeller speed in rpm\n",
+      "P2=2.23#Static pressure at impeller exit in bar\n",
+      "T01=288#The inlet stagnation temperature in K\n",
+      "P01=1.013#The inlet stagnation pressure in bar\n",
+      "C1=91.5#Velocity of air leaving the guide vanes in m/s\n",
+      "a11=70#The angle at which air leaves the guide vanes in degrees\n",
+      "r=1.4#The ratio of specific heats of air\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",
+      "\n",
+      "#calculations\n",
+      "Cx1=C1*cos(a11*pi/180)#Inlet absolute velocity of air in tangential direction in m/s\n",
+      "Ca1=Cx1*tan(a11*pi/180)#Radial component of absolute velocity at inlet in m/s\n",
+      "U1=(3.14*D1*N)/(60)#Peripheral velocity of impeller at inlet in m/s\n",
+      "Wx1=U1-Cx1#Relative whirl component of velocity at inlet in m/s\n",
+      "W1=((Wx1**2)+(Ca1**2))**(1/2)#Relative velocity at inlet in m/s\n",
+      "T1=T01-((C1**2)/(2*Cp))#The inlet air temperature in K\n",
+      "a1=(r*R*T1)**(1/2)#The velocity of air in m/s\n",
+      "M1r=W1/a1#Initial relative mach number\n",
+      "U2=(3.14*D2*N)/60#Peripheral velocity of impeller top at exit in m/s\n",
+      "W=(ss*U2**2)-(U1*Cx1)#Work done by the compressor in kJ/kg\n",
+      "T02=(W/Cp)+T01#The outlet stagnation temperature in K\n",
+      "Cx21=ss*U2#Absolute whirl component of velocity with slip consideration in m/s\n",
+      "C2=((Cx21**2)+(Cr2**2))**(1/2)#The absolute velocity of air at exit in m/s\n",
+      "T2=T02-((C2**2)/(2*Cp))#The exit temperature of air in K\n",
+      "P02=P2*(T02/T2)**(r/(r-1))#The exit stagnation pressure of compressor in bar\n",
+      "nc=(T01/(T02-T01))*(((P02/P01)**((r-1)/r))-1)#Total head isentropic efficiency\n",
+      "\n",
+      "#output\n",
+      "print '(1)The inlet relative mach number is %3.3f\\n(2)The impeller total head efficiency is %0.1f %%'%(M1r,nc*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(1)The inlet relative mach number is 0.732\n",
+        "(2)The impeller total head efficiency is 90.9 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 4
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 3.5 Page 100"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "N=16500#The running speed ofradial blade of a centrifugal compressor in rpm\n",
+      "P=4#The total pressure ratio\n",
+      "P01=1#The atmospheric pressure in bar\n",
+      "T01=298#THe atmospheric temperature in K\n",
+      "Dh=0.16#The hub diameter at impeller eye in m\n",
+      "Ca=120#The axial velocity at inlet in m/s\n",
+      "C1=Ca#The absolute velocity at inlet in m/s\n",
+      "sp=0.7#The pressure coefficient\n",
+      "C3=120#The absolute velocity at diffuser exit in m/s\n",
+      "m=8.3#The mass flow rate in kg/s\n",
+      "nc=0.78#The adiabatic total-to-total efficiency\n",
+      "r=1.4#The ratio of specific heats of air\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",
+      "\n",
+      "#calculations\n",
+      "T1=T01-((C1**2)/(2*Cp))#The inlet temperature in K\n",
+      "P1=P01*(T1/T01)**(r/(r-1))#The inlet pressure in bar\n",
+      "d1=(P1*10**5)/(R*T1)#The inlet density of air in kg/m**3\n",
+      "Dt=(((4*m)/(3.14*d1*Ca))+(0.16**2))**(1/2)#The eye tip diameter in m\n",
+      "T=((T01)*((P**((r-1)/r))-1))/nc#The overall change in temperature in K\n",
+      "ssps=sp/nc#The product of slip factor and power factor\n",
+      "U2=(T*Cp/ssps)**(1/2)#Peripheral velocity of impeller top at exit in m/s\n",
+      "D2=(U2*60)/(3.14*N)#The impeller tip diameter in m\n",
+      "Uh=(3.14*Dh*N)/60#Peripheral velocity of eye hub in m/s\n",
+      "bh=degrees(atan(C1/Uh))#Blade angle at eye hub in degree\n",
+      "Ut=(3.14*Dt*N)/60#Peripheral velocity of eye tip in m/s\n",
+      "bt=degrees(atan(C1/Ut))#Blade angle at eye tip in degree\n",
+      "T03=T01+T#Temperature at the exit in K\n",
+      "T3=T03-((C3**2)/(2*Cp))#Exit static temperature in K\n",
+      "P3=(P*P01)*(T3/T03)**(r/(r-1))#Exit static pressure in bar\n",
+      "W=m*Cp*(T03-T01)*10**-6#Power required to drive the compressor in mW\n",
+      "#output\n",
+      "print '(a)The main dimensions of the impeller are\\n    (1)Eye tip diameter is %3.3f m\\n    (2)Impeller tip diameter is %3.3f m\\n    (3)Blade angle at the eye hub is %3.2f degree\\n       Blade angle at the eye tip is %3.2f degree\\n(b)    (1)The static exit temperature is %3.1f K\\n    (2)The static exit pressure is %3.3f bar\\n(c)The power required is %3.3f mW'%(Dt,D2,bh,bt,T3,P3,W)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The main dimensions of the impeller are\n",
+        "    (1)Eye tip diameter is 0.325 m\n",
+        "    (2)Impeller tip diameter is 0.528 m\n",
+        "    (3)Blade angle at the eye hub is 40.98 degree\n",
+        "       Blade angle at the eye tip is 23.15 degree\n",
+        "(b)    (1)The static exit temperature is 476.5 K\n",
+        "    (2)The static exit pressure is 3.796 bar\n",
+        "(c)The power required is 1.549 mW\n"
+       ]
+      }
+     ],
+     "prompt_number": 5
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 3.6 Page 102"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import sin\n",
+      "#input data\n",
+      "Dt=0.25#Tip diameter of the eye in m\n",
+      "Dh=0.1#Hub diameter of the eye in m\n",
+      "N=120#Speed of the compressor in rps\n",
+      "m=5#Mass of the air handled in kg/s\n",
+      "P01=102#Inlet stagnation pressure in kPa\n",
+      "T01=335#Inlet total temperature in K\n",
+      "r=1.4#The ratio of specific heats of air\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",
+      "\n",
+      "#calculations\n",
+      "d1=(P01*10**3)/(R*T01)#Density at the inlet of inducer in kg/m**3\n",
+      "Dm=(Dh+Dt)/2#Mean impeller diameter in m\n",
+      "b=(Dt-Dh)/2#Impeller blade height in m\n",
+      "C1=m/(d1*3.14*Dm*b)#Axial velocity component at the inlet in m/s\n",
+      "T11=T01-((C1**2)/(2*Cp))#Inlet temperature in K\n",
+      "P11=P01*(T11/T01)**(r/(r-1))#Inlet pressure in kPa\n",
+      "d11=(P11*10**3)/(R*T11)#Inlet density with mean impeller diameter an blade height in kg/m**3\n",
+      "C11=m/(d11*3.14*Dm*b)#Axial velocity component at inlet using mean blade values in m/s\n",
+      "T12=T01-((C1**2)/(2*Cp))#Initial temperature using modified axial velocity in K\n",
+      "P12=P01*(T12/T01)**(r/(r-1))#Initial pressure at inlet usin modified axial velocity in kPa\n",
+      "d12=(P12*10**3)/(R*T12)#Inlet density with modified axial velocity in kg/m**3\n",
+      "C12=m/(d12*3.14*Dm*b)#Axial velocity component at inlet using modified axial velocity in m/s\n",
+      "U1=3.14*Dm*N#Peripheral velocity of impeller at inlet in m/s\n",
+      "b1=degrees(atan(C12/U1))#The blade angle at impeller inlet in degree\n",
+      "W11=C12/sin(b1*pi/180)#Relative velocity at inlet in m/s\n",
+      "Mr11=W11/(r*R*T12)**(1/2)#Initial relative mach number\n",
+      "Ca=C12#Axial velocity at IGV in m/s\n",
+      "W12=Ca#Relative velocity at inlet usin IGV in m/s\n",
+      "a1=degrees(atan(Ca/U1))#Air angle at IGV exit in degree\n",
+      "C13=Ca/sin(a1*pi/180)#The velocity of flow of air at inlet in m/s\n",
+      "T13=T01-((C13**2)/(2*Cp))#Initial temperature using IGV in K\n",
+      "Mr12=W12/(r*R*T13)**(1/2)#Initial relative mach number using IGV \n",
+      "\n",
+      "#output5\n",
+      "print '(1)Without using IGV\\n    (a)The air angle at inlet of inducer blade is %3.2f degree\\n    (b)The inlet relative mach number is %3.3f\\n(2)With using IGV\\n    (a))The air angle at inlet of inducer blade is %3.2f degree\\n    (b)The inlet relative mach number is %3.3f'%(b1,Mr11,a1,Mr12)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(1)Without using IGV\n",
+        "    (a)The air angle at inlet of inducer blade is 61.23 degree\n",
+        "    (b)The inlet relative mach number is 0.377\n",
+        "(2)With using IGV\n",
+        "    (a))The air angle at inlet of inducer blade is 61.23 degree\n",
+        "    (b)The inlet relative mach number is 0.332\n"
+       ]
+      }
+     ],
+     "prompt_number": 6
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 3.7 Page 105"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "Cr2=28#Radial component of velocity at impeller exit in m/s\n",
+      "ss=0.9#The slip factor\n",
+      "U2=350#The impeller tip speed in m/s\n",
+      "A=0.08#The impeller area in m**2\n",
+      "nc=0.9#Total head isentropic efficiency\n",
+      "T01=288#The ambient air temperature in K\n",
+      "P01=1#The ambient air pressure in bar\n",
+      "r=1.4#The ratio of specific heats of air\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",
+      "\n",
+      "#calculations\n",
+      "Cx2=ss*U2#outlet absolute velocity of air in tangential direction in m/s\n",
+      "C2=((Cx2**2)+(Cr2**2))**(1/2)#Axial velocity component at the outlet in m/s\n",
+      "T=(ss*(U2**2))/Cp#Total change in temperature in K\n",
+      "T02=T+T01#The final ambient air temperature in K\n",
+      "T2=T02-((C2**2)/(2*Cp))#The actual final air temperature in K\n",
+      "M2=(C2)/(r*R*T2)**(1/2)#Exit absolute mach number\n",
+      "P=((1+(ss*T/T01))**(r/(r-1)))#The overall pressure ratio\n",
+      "P02=P*P01#The final ambient pressure in bar\n",
+      "P2=P02*(T2/T02)**(r/(r-1))#The absolute final pressure in bar\n",
+      "d2=(P2*10**5)/(R*T2)#The final density of air at exit in kg/m**3\n",
+      "m=d2*A*Cr2#The mass flow rate in kg/s\n",
+      "\n",
+      "#output\n",
+      "print '(a)The exit absolute mach number is %3.4f\\n(b)The mass flow rate is %3.4f kg/s'%(M2,m)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The exit absolute mach number is 0.8458\n",
+        "(b)The mass flow rate is 3.9423 kg/s\n"
+       ]
+      }
+     ],
+     "prompt_number": 7
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 3.8 Page 107"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "Dh=0.175#Hub diameter of the eye in m\n",
+      "Dt=0.3125#Tip diameter of the eye in m\n",
+      "m=20#Mass of the air handled in kg/s\n",
+      "N=16000#Speed of the compressor in rpm\n",
+      "T01=288#The ambient air temperature in K\n",
+      "P01=100#The ambient air pressure in kPa\n",
+      "Ca=152#The axial component of inlet velocity of eye in m/s\n",
+      "r=1.4#The ratio of specific heats of air\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",
+      "\n",
+      "\n",
+      "#calculations\n",
+      "A=(3.14/4)*((Dt**2)-(Dh**2))#Annulus area of flow at the impeller eye in m**2\n",
+      "Ut=(3.1415*Dt*N)/60#Impeller eye tip speed in m/s\n",
+      "Uh=(3.1415*Dh*N)/60#Impeller eye hub speed in m/s\n",
+      "a1=90-20#Blade angle at inlet in degree \n",
+      "C1=Ca/sin(a1*pi/180)#The air entry velocity into the impeller eye in m/s\n",
+      "T1=T01-((C1**2)/(2*Cp))#The actual inlet air temperature in K\n",
+      "P1=P01*(T1/T01)**(r/(r-1))#The actual inlet air pressure in kPa\n",
+      "d1=P1/(R*T1)#The initial density of air at entry in kg/m**3\n",
+      "b1h=degrees(atan(Ca/(Uh-(Ca/tan(a1*pi/180)))))#Impeller angle at the hub in degree\n",
+      "b1t=degrees(atan(Ca/(Ut-(Ca/tan(a1*pi/180)))))#Impeller angle at the tip of eye in degree\n",
+      "Cx1=Ca/tan(a1*pi/180)#Inlet absolute velocity of air in tangential direction in m/s\n",
+      "Wx1=Ut-Cx1#Relative whirl component of velocity at inlet in m/s\n",
+      "W1=((Wx1**2)+(Ca**2))**(1/2)#Relative velocity at inlet in m/s\n",
+      "Mr1=W1/(r*R*T1)**(1/2)#Maximum mach number at the eye\n",
+      "\n",
+      "#output\n",
+      "print '(a)\\n    (1)The impeller eye tip speed is %3.2f m/s\\n    (2)The impeller eye hub speed is %3.2f m/s\\n    (3)The impeller angle at the hub is %i degree\\n    (4)Impeller angle at the tip of eye is %3.2f degree\\n(b)The maximum mach number at the eye is %3.2f'%(Ut,Uh,b1h,b1t,Mr1)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)\n",
+        "    (1)The impeller eye tip speed is 261.79 m/s\n",
+        "    (2)The impeller eye hub speed is 146.60 m/s\n",
+        "    (3)The impeller angle at the hub is 59 degree\n",
+        "    (4)Impeller angle at the tip of eye is 36.36 degree\n",
+        "(b)The maximum mach number at the eye is 0.77\n"
+       ]
+      }
+     ],
+     "prompt_number": 8
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 3.9 Page 109"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "P1=100#The air in take pressure in kPa\n",
+      "T1=309#The air in take temperature in K\n",
+      "H=0.750#Pressure head developed in mm W.G\n",
+      "P=33#Input power to blower in kW\n",
+      "nb=0.79#Blower efficiency\n",
+      "nm=0.83#Mechanical efficiency\n",
+      "r=1.4#The ratio of specific heats of air\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",
+      "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",
+      "d=(P1*10**3)/(R*T1)#Density of air flow at inlet in kg/m**3\n",
+      "dP=dw*g*H#Total change in pressure in N/m**2\n",
+      "IW=dP/d#Ideal work done in J/kg\n",
+      "Wm=IW/nb#Actual work done per unit mass flow rate in J/kg\n",
+      "W=P*nm#Actual power input in kW\n",
+      "m=(W*10**3)/Wm#Mass flow rate in kg/s\n",
+      "Q=m/d#Volume flow rate in m**3/s\n",
+      "P2=P1+(dP/10**3)#The exit pressure of air in kPa\n",
+      "T2=T1+(Wm/(Cp))#The exit temperature of air in K\n",
+      "\n",
+      "#output\n",
+      "print '(a)The mass flow rate of air is %3.3f kg/s\\n(b)The volume flow rate of air is %3.2f m**3/s\\n(c)\\n    (1)The exit pressure of air is %3.2f kPa\\n    (2)The exit temperature of air is %3.2f K'%(m,Q,P2,T2)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The mass flow rate of air is 3.316 kg/s\n",
+        "(b)The volume flow rate of air is 2.94 m**3/s\n",
+        "(c)\n",
+        "    (1)The exit pressure of air is 107.36 kPa\n",
+        "    (2)The exit temperature of air is 317.22 K\n"
+       ]
+      }
+     ],
+     "prompt_number": 9
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 3.10 Page 110"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "H=0.075#Pressure developed by a fan in m W.G\n",
+      "D2=0.89#The impeller diameter in m\n",
+      "N=720#The running speed of the fan in rpm\n",
+      "b22=39#The blade air angle at the tip in degree\n",
+      "b2=0.1#The width of the impeller in m\n",
+      "Cr=9.15#The constant radial velocity in m/s\n",
+      "d=1.2#Density of air in kg/m**3\n",
+      "r=1.4#The ratio of specific heats of air\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",
+      "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",
+      "IW=(dw*g*H)/d#Ideal work done in J/kg\n",
+      "U2=(3.1415*D2*N)/60#The impeller tip speed in m/s\n",
+      "Wx2=Cr/tan(b22*pi/180)#Relative whirl component of velocity at outlet in m/s\n",
+      "Cx2=U2-(Wx2)#Outlet absolute velocity of air in tangential direction in m/s\n",
+      "Wm=U2*Cx2#Actual work done per unit mass flow rate in J/kg\n",
+      "nf=IW/Wm#Fan efficiency\n",
+      "Q=3.1415*D2*b2*Cr#The discharge of the air by fan in m**3/s\n",
+      "m=d*Q#Mass flow rate of the air by the fan in kg/s\n",
+      "W=m*Wm*10**-3#Power required to drive the fan in kW\n",
+      "R=1-(Cx2/(2*U2))#Stage reaction of the fan\n",
+      "sp=2*Cx2/U2#The pressure coefficient\n",
+      "\n",
+      "#output\n",
+      "print '(a)The fan efficiency is %0.1f %%\\n(b)The Discharge of air by the fan is %3.3f m**3/s\\n(c)The power required to drive the fan is %3.4f kW\\n(d)The stage reaction of the fan is %0.2f %%\\n(e)The pressure coefficient of the fan is %3.3f'%(nf*100,Q,W,R*100,sp)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The fan efficiency is 82.1 %\n",
+        "(b)The Discharge of air by the fan is 2.558 m**3/s\n",
+        "(c)The power required to drive the fan is 2.2919 kW\n",
+        "(d)The stage reaction of the fan is 66.84 %\n",
+        "(e)The pressure coefficient of the fan is 1.326\n"
+       ]
+      }
+     ],
+     "prompt_number": 10
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 3.11 Page 111"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "\n",
+      "b22=30#The blade air angle at the tip in degrees\n",
+      "D2=0.466#The impeller diameter in m\n",
+      "Q=3.82#The discharge of the air by fan in m**3/s\n",
+      "m=4.29#Mass flow rate of the air by the fan in kg/s\n",
+      "H=0.063#Pressure developed by a fan in m W.G\n",
+      "pi2=0.25#Flow coefficient at impeller exit\n",
+      "W=3#Power supplied to the impeller in kW\n",
+      "r=1.4#The ratio of specific heats of air\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",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "dw=10**3#Density of water in kg/m**3\n",
+      "\n",
+      "#calculations\n",
+      "IW=Q*dw*g*H*(10**-3)#Ideal work done in kW\n",
+      "nf=IW/W#Fan efficiency\n",
+      "U2=(((W*10**3)/m)/(1-(pi2/tan(b22*pi/180))))**(1/2)#The impeller tip speed in m/s\n",
+      "Cr2=pi2*U2#The radial velocity at exit in m/s\n",
+      "Cx2=U2-(Cr2/tan(b22*pi/180))#Outlet absolute velocity of air in tangential direction in m/s\n",
+      "sp=2*Cx2/U2#Presuure coefficient of the fan\n",
+      "R=1-(Cx2/(2*U2))#Degree of reaction of the fan\n",
+      "N=(U2*60)/(3.141592*D2)#Rotational speed of the fan in rpm\n",
+      "b2=Q/(3.14*D2*Cr2)#Impeller width at the exit in m\n",
+      "\n",
+      "#output\n",
+      "print '(a)The fan efficiency is %0.1f %%\\n(b)The pressure coefficient is %3.3f\\n(c)The degree of reaction of the fan is %0.1f %%\\n(d)The rotational speed of the fan is %3.1f rpm\\n(e)The impeller width at exit is %0.1f cm'%(nf*100,sp,R*100,N,b2*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The fan efficiency is 78.7 %\n",
+        "(b)The pressure coefficient is 1.134\n",
+        "(c)The degree of reaction of the fan is 71.7 %\n",
+        "(d)The rotational speed of the fan is 1439.3 rpm\n",
+        "(e)The impeller width at exit is 29.7 cm\n"
+       ]
+      }
+     ],
+     "prompt_number": 11
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 3.12 Page 113"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "N=3000#The running speed of the blower in rpm\n",
+      "D2=0.75#The impeller diameter in m\n",
+      "Cr2=57#The radial velocity at exit in m/s\n",
+      "Cx1=0#Inlet absolute velocity of air in tangential direction in m/s\n",
+      "DR=0.58#Degree of reaction of the blower\n",
+      "nc=0.75#Total-to-total efficiency\n",
+      "r=1.4#The ratio of specific heats of air\n",
+      "R=287#The universal gas constant in J/kg.K\n",
+      "Cp=1.005#The specific heat of air at constant pressure in J/kg.K\n",
+      "T01=298#The inlet stagnation temperature in K\n",
+      "P01=1*101.325#The inlet stagnation pressure in kPa\n",
+      "\n",
+      "#calculations\n",
+      "U2=(3.1415*D2*N)/60#The impeller tip speed in m/s\n",
+      "Cx2=2*(1-DR)*U2#Outlet absolute velocity of air in tangential direction in m/s\n",
+      "Wx2=U2-Cx2#Relative whirl component of velocity at outlet in m/s\n",
+      "b22=degrees(atan(Cr2/Wx2))#The blade air angle at the tip in degree\n",
+      "Wm=U2*Cx2*10**-3#Actual work done per unit mass flow rate when Cx1=0 in kW/(kg/s)\n",
+      "T=Wm/Cp#Total change in temperature in blower in K\n",
+      "P=(1+(nc*(T/T01)))**(r/(r-1))#Total pressure ratio in the blower\n",
+      "P02=P*P01#The outlet stagnation pressure from blower in kPa\n",
+      "\n",
+      "#output\n",
+      "print '(a)The exit blade angle is %3.1f degree\\n(b)The power input to the blower is %3.3f kW/(kg/s)\\n(c)The exit stagnation pressure is %3.2f kPa'%(b22,Wm,P02)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The exit blade angle is 71.7 degree\n",
+        "(b)The power input to the blower is 11.658 kW/(kg/s)\n",
+        "(c)The exit stagnation pressure is 112.06 kPa\n"
+       ]
+      }
+     ],
+     "prompt_number": 12
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 3.13 Page 114"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "D1=0.18#The impeller inner diameter in m\n",
+      "D2=0.2#The impeller outer diameter in m\n",
+      "C1=21#The absolute velocity at the entry in m/s\n",
+      "C2=25#The absolute velocity at the exit in m/s\n",
+      "W1=20#The relative velocity at the entry in m/s\n",
+      "W2=17#The relative velocity at the exit in m/s\n",
+      "N=1450#The running speed of the fan in rpm\n",
+      "m=0.5#The mass flow rate of the air in fan in kg/s\n",
+      "nm=0.78#The motor efficiency of the fan \n",
+      "d=1.25#The density of the air in kg/m**3\n",
+      "r=1.4#The ratio of specific heats of air\n",
+      "R=287#The universal gas constant in J/kg.K\n",
+      "Cp=1.005#The specific heat of air at constant pressure in J/kg.K\n",
+      "\n",
+      "#calculations\n",
+      "U1=(3.14*D1*N)/60#Peripheral velocity of impeller at inlet in m/s\n",
+      "U2=(3.14*D2*N)/60#The impeller tip speed in m/s\n",
+      "dH=(((U2**2)-(U1**2))/2)+(((W1**2)-(W2**2))/2)#The actual total rise in enthalpy in kJ/kg\n",
+      "dH0=dH+(((C2**2)-(C1**2))/2)#The stage total isentropic rise in enthalpy in kJ/kg\n",
+      "dP0=d*dH0#The stage total pressure rise in N/m**2\n",
+      "dP=d*dH#The actual total rise in pressure in N/m**2\n",
+      "R=dP/dP0#The degree of reaction of the  fan\n",
+      "W=m*(dH0)#The work done by the fan per second in W\n",
+      "P=W/nm#The power input to the fan in W\n",
+      "\n",
+      "#output\n",
+      "print '(a)The stage total pressure rise is %3.1f N/m**2\\n(b)The degree of reaction of the fan is %3.3f\\n(c)The power input to the fan is %3.1f W'%(dP0,R,P)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The stage total pressure rise is 211.7 N/m**2\n",
+        "(b)The degree of reaction of the fan is 0.457\n",
+        "(c)The power input to the fan is 108.6 W\n"
+       ]
+      }
+     ],
+     "prompt_number": 13
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 3.14 Page 116"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "dH=0.14#Rise in static pressure of the air by fan in m of water\n",
+      "N=650#The running speed of the fan in rpm\n",
+      "P=85*0.735#Power consumed by the fan in kW\n",
+      "H1=0.75#The static pressure of the air at the fan in m of Hg\n",
+      "T1=298#The static pressure at the fan of air in K\n",
+      "m=260#Mass flow rate of air in kg/min\n",
+      "dHg=13590#Density of mercury in kg/m**3\n",
+      "dw=1000#Density of water in kg/m**3\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "R=287#The universal gas constant in J/kg.K\n",
+      "\n",
+      "#calculations\n",
+      "P1=dHg*g*H1*10**-3#The inlet static pressure in kPa\n",
+      "dP=dw*g*dH*10**-3#The total change in static pressures at inlet and outlet in kPa\n",
+      "P2=P1+dP#The exit static pressure in kPa\n",
+      "d1=(P1*10**3)/(R*T1)#The inlet density of the air in kg/m**3\n",
+      "Q=m/d1#The volume flow rate of air in fan in m**3/min\n",
+      "\n",
+      "#output\n",
+      "print '(a)The exit static pressure of air in the fan is %3.2f kPa\\n(b)The volume flow rate of the air is %3.1f m**3/min'%(P2,Q)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The exit static pressure of air in the fan is 101.36 kPa\n",
+        "(b)The volume flow rate of the air is 222.4 m**3/min\n"
+       ]
+      }
+     ],
+     "prompt_number": 14
+    }
+   ],
+   "metadata": {}
+  }
+ ]
+}
\ No newline at end of file
diff --git a/Turbomachines_by_A._V._Arasu/Ch4.ipynb b/Turbomachines_by_A._V._Arasu/Ch4.ipynb
new file mode 100644
index 00000000..0af505f8
--- /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
diff --git a/Turbomachines_by_A._V._Arasu/Ch5.ipynb b/Turbomachines_by_A._V._Arasu/Ch5.ipynb
new file mode 100644
index 00000000..8d6309b4
--- /dev/null
+++ b/Turbomachines_by_A._V._Arasu/Ch5.ipynb
@@ -0,0 +1,1195 @@
+{
+ "metadata": {
+  "name": "",
+  "signature": "sha256:b3c6b5b9437eb9e3bff13119283daec451a9bdb3f3f492bbf38ecac5c3f69e9c"
+ },
+ "nbformat": 3,
+ "nbformat_minor": 0,
+ "worksheets": [
+  {
+   "cells": [
+    {
+     "cell_type": "heading",
+     "level": 1,
+     "metadata": {},
+     "source": [
+      "Chapter 5 - Axial flow steam & gas turbines"
+     ]
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 5.1 Page 211"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from __future__ import division\n",
+      "#input data\n",
+      "C1=500#Steam velocity in m/s\n",
+      "U=200#Blade speed in m/s\n",
+      "b2=(90-25)#Exit angle of moving blade measured in axial direction in degree\n",
+      "a1=(90-20)#Nozzle angle in axial direction in degree\n",
+      "m=5#Steam flow rate in kg/s\n",
+      "\n",
+      "print 'The scale of the velocity vector diagram is 1:50\\n\\nThe following values are obtained from the velocity vector diagram'\n",
+      "\n",
+      "b1=33#Moving blade inlet angle in degree\n",
+      "a2=56#Direction of steam at the exit in degree\n",
+      "C2=160#Exit velocity of the steam in m/s\n",
+      "Wx1=270#Inlet whirl velocity in m/s\n",
+      "Wx2=285#Exit whirl velocity in m/s\n",
+      "Ca1=175#Inlet axial velocity in m/s\n",
+      "Ca2=135#Exit axial velocity in m/s\n",
+      "\n",
+      "#calculations\n",
+      "Wm=U*(Wx1+Wx2)*10**-3#Work done per kg of steam in kW/kg\n",
+      "AT=m*(Ca1-Ca2)#Axial thrust in N\n",
+      "W=m*Wm#Power developed in kW\n",
+      "Ndia=((U*(Wx1+Wx2))/((C1**2)/2))#Diagram or blade efficiency \n",
+      "\n",
+      "#output\n",
+      "print '\\n\\n(a)Moving blade inlet angle is %3i degree\\n(b)\\n    Exit velocity of the steam is %3i m/s\\n    Direction of steam at the exit is %3i degree\\n(c)Work done per kg of steam is %3i kW/kg\\n(d)\\n    Axial thrust is %3i N\\n    Power developed is %3i kW\\n(e)Diagram or blade efficiency is %0.1f %%'%(b1,C2,a2,Wm,AT,W,Ndia*100)\n",
+      "# the answer in the textbook is not correct for axial thrust."
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "The scale of the velocity vector diagram is 1:50\n",
+        "\n",
+        "The following values are obtained from the velocity vector diagram\n",
+        "\n",
+        "\n",
+        "(a)Moving blade inlet angle is  33 degree\n",
+        "(b)\n",
+        "    Exit velocity of the steam is 160 m/s\n",
+        "    Direction of steam at the exit is  56 degree\n",
+        "(c)Work done per kg of steam is 111 kW/kg\n",
+        "(d)\n",
+        "    Axial thrust is 200 N\n",
+        "    Power developed is 555 kW\n",
+        "(e)Diagram or blade efficiency is 88.8 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 1
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 5.2 Page 213"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import sin, pi\n",
+      "#input data\n",
+      "U=300#Blade speed in m/s\n",
+      "a=20#Nozzle angle in degree\n",
+      "dhs=473#Isentropic heat drop in kJ/kg\n",
+      "Nn=0.85#Nozzle efficiency\n",
+      "W2W1=0.7#Blade velocity coefficient\n",
+      "nM=0.9#Mechanical efficiency\n",
+      "\n",
+      "#initial calculations\n",
+      "dh=Nn*dhs#Useful heat drop converted into kinetic energy in kJ/kg\n",
+      "C1=(2*1000*dh)**(1/2)#Velocity of steam at exit from nozzle in m/s\n",
+      "\n",
+      "print 'The scale of the velocity vector diagram is 1:100\\n\\nThe following values are obtained from the velocity vector diagram'\n",
+      "\n",
+      "Ca1=310#Inlet axial velocity in m/s\n",
+      "Ca2=210#Exit axial velocity in m/s\n",
+      "Wx1=550#Inlet whirl velocity in m/s\n",
+      "Wx2=380#Exit whirl velocity in m/s\n",
+      "W1=620#inlet Blade velocity in m/s\n",
+      "\n",
+      "#calculations\n",
+      "W2=W2W1*W1#Exit bladde velocity in m/s\n",
+      "AT=Ca1-Ca2#Axial thrust in N/kg\n",
+      "Wm=U*(Wx1+Wx2)*10**-3#Work developed per kg of steam/sec in kW/(kg/s)\n",
+      "P=Wm*nM#Power developed per kg of steam/sec in kW/(kg/s)\n",
+      "m=3600/P#Steam rate per kW.hr in kg\n",
+      "Ndia=((U*(Wx1+Wx2))/((C1**2)/2))#Diagram or blade efficiency \n",
+      "MNdia=(sin((90-a)*pi/180))**(2)#Maximum blade efficiency under optimum conditions \n",
+      "Ns1=Wm/dhs#Stage efficiency\n",
+      "Ns2=Ndia*Nn#Stage efficiency in other method\n",
+      "E=(((W1**2)-(W2**2))/2)*10**-3#Energy loss in blade friction in kJ/kg\n",
+      "\n",
+      "#output\n",
+      "print '\\n\\n(a)Axial thrust is %3i N/kg\\n(b)\\n    Work developed per kg of steam/sec is %3i kW/(kg/s)\\n    Power developed per kg of steam/sec is %3.1f kW/(kg/s)\\n    Steam rate per kW.hr is %3.1f kg\\n(c)\\n    Diagram or blade efficiency is %0.1f %%\\n    Maximum blade efficiency under optimum conditions is %0.1f %%\\n    Stage efficiency is %0.2f %%\\n(d)Energy loss in blade friction is %3.3f kJ/kg'%(AT,Wm,P,m,Ndia*100,MNdia*100,Ns1*100,E)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "The scale of the velocity vector diagram is 1:100\n",
+        "\n",
+        "The following values are obtained from the velocity vector diagram\n",
+        "\n",
+        "\n",
+        "(a)Axial thrust is 100 N/kg\n",
+        "(b)\n",
+        "    Work developed per kg of steam/sec is 279 kW/(kg/s)\n",
+        "    Power developed per kg of steam/sec is 251.1 kW/(kg/s)\n",
+        "    Steam rate per kW.hr is 14.3 kg\n",
+        "(c)\n",
+        "    Diagram or blade efficiency is 69.4 %\n",
+        "    Maximum blade efficiency under optimum conditions is 88.3 %\n",
+        "    Stage efficiency is 58.99 %\n",
+        "(d)Energy loss in blade friction is 98.022 kJ/kg\n"
+       ]
+      }
+     ],
+     "prompt_number": 5
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 5.3 Page 215"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "P1=5#Input pressure of steam in bar\n",
+      "P2=3#Exhaust pressure of steam in bar\n",
+      "C0=75#Carry over velocity of steam in m/s\n",
+      "a1=20#Nozzle angle in degree\n",
+      "UC1=0.4#The direction of blade rotation and blade speed ratio\n",
+      "b2=20#Blade exit angle in degree\n",
+      "m=2.5#Steam flow rate in kg/s\n",
+      "W=206#Power Output of the stage in kW\n",
+      "Nn=0.9#Efficiency of the nozzle\n",
+      "\n",
+      "print 'Assuming isentropic expansion the enthalpy drop can be found from steam table\\n\\nThe following values are obtained from steam tables'\n",
+      " \n",
+      "h1=2747.5#Enthalpy at initial pressure in kJ/kg\n",
+      "s1=6.819#Entropy at initial pressure in kJ/kg.K\n",
+      "s2=s1#Entropy at final pressure in kJ/kg.K\n",
+      "sfp2=1.647#Entropy of fliud at final pressure in kJ/kg.K\n",
+      "sfgp2=5.367#Entropy of fliud-gas mixture at final pressure in kJ/kg.K\n",
+      "hfg=2170.1#Enthalpy of fliud-gas mixture in kJ/kg\n",
+      "hf=551.5#Enthalpy of fliud in kJ/kg\n",
+      "\n",
+      "print '\\n\\nThe scale of the velocity vector diagram is 1:50\\n\\nThe following values are obtained from the velocity vector diagram'\n",
+      "\n",
+      "W1=280#Relative velocity at inlet in m/s\n",
+      "W2=240#Relative velocity at exit in m/s\n",
+      "\n",
+      "#calculations\n",
+      "x2=(s2-sfp2)/sfgp2#The percentage of wet steam \n",
+      "h2s=hf+(x2*hfg)#The isentropic enthalpy at the second stage in kJ/kg\n",
+      "dhs=h1-h2s#Isentropic heat drop in kJ/kg\n",
+      "C1=((2000*Nn*dhs)+(C0**2))**(1/2)#Velocity of steam at exit from nozzle in m/s\n",
+      "U=UC1*C1#Blade speed in m/s\n",
+      "Wx1Wx2=(W*10**3)/(m*U)#The sum of whirl components of velocity in m/s\n",
+      "Ndia=(U*Wx1Wx2)/((C1**2)/2)#Diagram efficiency \n",
+      "RV=W2/W1#Relative velocity ratio \n",
+      "E=dhs+((C0**2)/2000)#Energy supplied per kg in kJ/kg\n",
+      "Ns1=(U*Wx1Wx2)/(E*10**3)#Stage efficiency\n",
+      "Ns2=Ndia*Nn#Stage efficiency in other method\n",
+      "\n",
+      "#output\n",
+      "print '\\n\\n(a)Velocity of steam at exit from nozzle is %3.2f m/s\\n(b)Diagram efficiency is %0.2f\\n(c)Relative velocity ratio is %3.3f\\n(d)\\n    Stage efficiency in method 1 is %0.2f\\n    Stage efficiency in method 2 is %0.2f'%(C1,Ndia*100,RV,Ns1*100,Ns2*100)\n",
+      "# the answer in the textbook is not accurate."
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "Assuming isentropic expansion the enthalpy drop can be found from steam table\n",
+        "\n",
+        "The following values are obtained from steam tables\n",
+        "\n",
+        "\n",
+        "The scale of the velocity vector diagram is 1:50\n",
+        "\n",
+        "The following values are obtained from the velocity vector diagram\n",
+        "\n",
+        "\n",
+        "(a)Velocity of steam at exit from nozzle is 440.65 m/s\n",
+        "(b)Diagram efficiency is 84.87\n",
+        "(c)Relative velocity ratio is 0.857\n",
+        "(d)\n",
+        "    Stage efficiency in method 1 is 76.61\n",
+        "    Stage efficiency in method 2 is 76.39\n"
+       ]
+      }
+     ],
+     "prompt_number": 6
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 5.4 Page 218"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "C1=600#Velocity of steam at exit from nozzle in m/s\n",
+      "U=120#Blade speed in m/s\n",
+      "a1=16#Nozzle angle in degree\n",
+      "b2=18#Discharge angle for first moving ring in degree \n",
+      "a11=21#Discharge angle for the fixed ring in degree \n",
+      "b22=35#Discharge angle for the second moving ring in degree\n",
+      "Wr=0.9#Blade velocity coefficient\n",
+      "m=1#Mass flow rate in kg/s\n",
+      "\n",
+      "print '\\n\\nThe scale of the velocity vector diagram is 1:50\\n\\nThe following values are obtained from the velocity vector diagram'\n",
+      "\n",
+      "W1=485#Relative velocity at inlet for first stage in m/s\n",
+      "W2=Wr*W1#Relative velocity for first stage at exit in m/s\n",
+      "Wx1=460#Inlet whirl  velocity for first stage in m/s\n",
+      "Wx2=410#Exit whirl velocity for first stage  in m/s\n",
+      "Ca1=170#Inlet axial velocity for first stage  in m/s\n",
+      "Ca2=135#Exit axial velocity for first stage in m/s\n",
+      "C2=325#Exit velocity of the steam for first stage in m/s\n",
+      "b1=20#Blade inlet angle for first row of moving blade in degree\n",
+      "C11=Wr*C2#Steam velocity at inlet to second row of moving blades in m/s\n",
+      "W12=190#Relative velocity at inlet for second stage in m/s\n",
+      "W22=Wr*W12#Relative velocity at exit for second stage in m/s\n",
+      "Wx11=155#Inlet whirl velocity  for second stage in m/s\n",
+      "Wx22=140#Exit whirl velocity for second stage  in m/s\n",
+      "Ca11=110#Inlet axial velocity for second stage  in m/s\n",
+      "Ca22=100#Exit axial velocity for second stage in m/s\n",
+      "b11=35#Blade inlet angle for second row of moving blade in degree\n",
+      "dWx1=Wx1+Wx2#Driving force for first stage in m/s\n",
+      "dWx11=Wx11+Wx22#Driving force for second stage in m/s\n",
+      "dW=(dWx1+dWx11)*1#Total driving force for unit mass flow rate in N\n",
+      "AT1=Ca1-Ca2#Axial thrust for first stage in m/s\n",
+      "AT2=Ca11-Ca22#Axial thrust for second stage in m/s\n",
+      "AT=(AT1+AT2)*1#Total axial thrust for unit mass flow rate in N\n",
+      "DP=m*U*(dWx1+dWx11)*10**-3#Diagram power in kW\n",
+      "DE=(U*(dWx1+dWx11))/((C1**2)/2)#Diagram efficiency\n",
+      "MDE=(sin((90-a1)*pi/180))**2#Maximum  diagram efficiency\n",
+      "\n",
+      "#output\n",
+      "print '\\n\\n(a)\\n    Blade inlet angle for first row of moving blade is %3.i degree\\n    Blade inlet angle for second row of moving blade is %3i degree\\n(b)\\n    Driving force for first stage is %3i m/s\\n    Driving force for second stage is %3i m/s\\n    Total driving force for unit mass flow rate is %3i N\\nTotal axial thrust for unit mass flow rate is %3i N\\n(c)Diagram power is %3.1f kW\\n(d)Diagram efficiency is %0.1f\\n(e)Maximum  diagram efficiency is %0.1f'%(b1,b11,dWx1,dWx11,dW,AT,DP,DE*100,MDE*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "\n",
+        "\n",
+        "The scale of the velocity vector diagram is 1:50\n",
+        "\n",
+        "The following values are obtained from the velocity vector diagram\n",
+        "\n",
+        "\n",
+        "(a)\n",
+        "    Blade inlet angle for first row of moving blade is  20 degree\n",
+        "    Blade inlet angle for second row of moving blade is  35 degree\n",
+        "(b)\n",
+        "    Driving force for first stage is 870 m/s\n",
+        "    Driving force for second stage is 295 m/s\n",
+        "    Total driving force for unit mass flow rate is 1165 N\n",
+        "Total axial thrust for unit mass flow rate is  45 N\n",
+        "(c)Diagram power is 139.8 kW\n",
+        "(d)Diagram efficiency is 77.7\n",
+        "(e)Maximum  diagram efficiency is 92.4\n"
+       ]
+      }
+     ],
+     "prompt_number": 7
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 5.5 Page 220"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import cos\n",
+      "#input data\n",
+      "C1=100#Velocity of steam at exit from nozzle in m/s\n",
+      "h=0.04#Mean blade height in m\n",
+      "b2=20#Exit angle of moving blade in degree\n",
+      "CaU=3/4#Ratio of flow velocity and blade speed at mean radius\n",
+      "m=10000/3600#steam flow rate in kg/s\n",
+      "\n",
+      "#calculations\n",
+      "a1=b2#Nozzle angle in degree\n",
+      "Ca=C1*cos((90-a1)*pi/180)#Flow velocity in m/s\n",
+      "U=Ca/CaU#Mean blade velocity in m/s\n",
+      "v=0.60553#Specific volume of steam from steam table at 3 bar with dry saturated steam in m**3/kg\n",
+      "A=(m*v)/Ca#Annulus area in m**2\n",
+      "D=A/(3.1415*h)#Mean blade diameter in m\n",
+      "N=(U*60)/(3.14*D)#Rotor speed in rpm\n",
+      "\n",
+      "print '\\n\\nThe scale of the velocity vector diagram is 1:10\\n\\nThe following values are obtained from the velocity vector diagram'\n",
+      "\n",
+      "W1=59#Relative velocity at inlet for first stage in m/s\n",
+      "Wx1Wx2=142#Sum of whirl components of velocity in m/s\n",
+      "DP=m*U*Wx1Wx2*10**-3#Diagram power in kW\n",
+      "Wm=U*(Wx1Wx2)#Work done per kg of steam in kJ/kg\n",
+      "W2=C1#Relative velocity at exit for first stage in m/s\n",
+      "E=((C1**2)/2)+(((W2**2)-(W1**2))/2)#Energy input per kg in kJ/kg when W2=C1\n",
+      "Ndia=Wm/E#Diagram efficiency \n",
+      "RV=(W2-W1)/W1#Percentage increase in relative velocity \n",
+      "dH=((W2**2)-(W1**2))/2*10**-3#Enthalpy drop in the moving blades in kJ/kg\n",
+      "H=2*dH#Total enthalpy drop in two stages in kJ/kg\n",
+      "\n",
+      "#output\n",
+      "print '\\n\\n(a)The rotor speed is %3i rpm\\n(b)The diagram power is %3.2f kW\\n(c)The diagram efficiency is %0.1f\\n(d)Percentage increase in relative velocity is %0.1f\\n(e)\\n    Enthalpy drop in the moving blades is %3.3f kJ/kg\\n    Total enthalpy drop in two stages is %3.3f kJ/kg'%(N,DP,Ndia*100,RV*100,dH,H)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "\n",
+        "\n",
+        "The scale of the velocity vector diagram is 1:10\n",
+        "\n",
+        "The following values are obtained from the velocity vector diagram\n",
+        "\n",
+        "\n",
+        "(a)The rotor speed is 2226 rpm\n",
+        "(b)The diagram power is 17.99 kW\n",
+        "(c)The diagram efficiency is 78.4\n",
+        "(d)Percentage increase in relative velocity is 69.5\n",
+        "(e)\n",
+        "    Enthalpy drop in the moving blades is 3.260 kJ/kg\n",
+        "    Total enthalpy drop in two stages is 6.519 kJ/kg\n"
+       ]
+      }
+     ],
+     "prompt_number": 10
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 5.6 Page 222"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "R=0.5#Degree of reaction\n",
+      "P1=14#Initial pressure in bar\n",
+      "T1=588#Initial temperature in K\n",
+      "P2=0.14#Final pressure in bar\n",
+      "Ns=0.75#Stage efficiency \n",
+      "RF=1.04#Reheat factor \n",
+      "N=20#No. of stages\n",
+      "W=11770#Total power output in kW\n",
+      "a1=20#Exit blade angle in degree\n",
+      "hD=1/12#Ratio of blade height to blade mean diameter \n",
+      "\n",
+      "#calculations\n",
+      "hs1=3080#Isentropic enthalpy at initial condition from mollier chart in kJ/kg\n",
+      "hs2=2270#Isentropic enthalpy at final condition from mollier chart in kJ/kg\n",
+      "dhs=hs1-hs2#Isentropic enthalpy change in kJ/kg\n",
+      "Nt=Ns*RF#Overall efficiency\n",
+      "dh=Nt*dhs#Actual enthalpy drop in kJ/kg\n",
+      "hs=dh/N#Enthalpy drop per stage in kJ/kg\n",
+      "m=W/dh#Mass flow rate in kg/s\n",
+      "C11=1.43*1#Velocity of steam at exit from nozzle in m/s in terms of U for 0.5 degree of reaction\n",
+      "Wm=1*((2*C11*sin((90-a1)*pi/180))-1)#Work done per mass of steam in terms of U**2 in kJ/kg\n",
+      "U=((hs*10**3)/Wm)**(1/2)#Mean blade velocity in m/s  as work done equals enthalpy drop per stage \n",
+      "C1=1.43*U#Velocity of steam at exit from nozzle in m/s \n",
+      "Ca=C1*cos((90-a1)*pi*180)#Flow velocity in m/s\n",
+      "v=1.618#Specific volume of steam from steam table at 1.05 bar with dry saturated steam in m**3/kg\n",
+      "D=((m*v)/(hD*3.14*Ca))**(1/2)#Blade mean diameter in m\n",
+      "N=(U*60)/(3.14*D)#Rotor speed in rpm\n",
+      "\n",
+      "#output\n",
+      "print '(a)Mass flow rate of steam is %3.2f kg/s\\n(b)Mean blade velocity is %3.1f m/s \\n(c)Blade mean diameter is %3.3f m \\n(d)Rotor speed is %3i rpm'%(m,U,D,N)\n",
+      "# the answer in the textbook is not correct."
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Mass flow rate of steam is 18.63 kg/s\n",
+        "(b)Mean blade velocity is 136.8 m/s \n",
+        "(c)Blade mean diameter is 0.767 m \n",
+        "(d)Rotor speed is 3407 rpm\n"
+       ]
+      }
+     ],
+     "prompt_number": 11
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 5.7 Page 224"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import tan, pi, degrees, atan\n",
+      "#input data\n",
+      "rh=0.225#Blade roof radius in m\n",
+      "rt=0.375#Blade tip radius in m\n",
+      "b1m=45#Inlet angle of the rotor blade at mid height in degree\n",
+      "a1m=76#Outlet angle of the nozzle blade at mid height in degree\n",
+      "b2m=75#Outlet angle of the rotor blade at mid height in degree\n",
+      "N=6000#Speed of turbine in rpm\n",
+      "\n",
+      "#calculations\n",
+      "rm=(rh+rt)/2#Mean radius in m\n",
+      "Um=(2*3.14*rm*N)/60#Mean blade speed at mean radius in m/s\n",
+      "Ca=Um/((tan(a1m*pi/180))-(tan(b1m*pi/180)))#Flow velocity in m/s\n",
+      "Cx1m=Ca*tan(a1m*pi/180)#Velocity of whirl at inlet at mid height in m/s\n",
+      "Cx2m=Ca*tan(b2m*pi/180)-Um#Velocity of whirl at inlet at mid height in m/s\n",
+      "Cx1h=(Cx1m*rm)/rh#Velocity of whirl at inlet at hub height in m/s\n",
+      "a1h=degrees(atan(Cx1h/Ca))#Inlet angle of the nozzle blade at hub height in degree\n",
+      "Uh=(2*3.1415*rh*N)/60#Mean blade speed at hub in m/s\n",
+      "b1h=degrees(atan(tan(a1h*pi/180)-(Uh/Ca)))#Inlet angle of the rotor blade at hub in degree\n",
+      "Cx2h=Cx2m*rm/rh#Velocity of whirl at outlet at hub in m/s\n",
+      "b2h=degrees(atan((Uh+Cx2h)/Ca))#Outlet angle of the rotor blade at hub in degree\n",
+      "Cx1t=Cx1m*rm/rt#Velocity of whirl at inlet at tip in m/s\n",
+      "a1t=degrees(atan(Cx1t/Ca))#Inlet angle of the nozzle blade at tip height in degree\n",
+      "Ut=(2*3.14*rt*N)/60#Mean blade speed at tip in m/s\n",
+      "b1t=degrees(atan(tan(a1t*pi/180)-(Ut/Ca)))#Inlet angle of the rotor blade at tip in degree\n",
+      "Cx2t=Cx2m*rm/rt#Velocity of whirl at outlet at tip in m/s\n",
+      "b2t=degrees(atan((Ut+Cx2t)/Ca))#Outlet angle of the rotor blade at hub in degree\n",
+      "Rh=(Ca/(2*Uh))*(tan(b2h*pi/180)-tan(b1h*pi/180))#Degree of reaction at hub\n",
+      "Rt=(Ca/(2*Ut))*(tan(b2t*pi/180)-tan(b1t*pi/180))#Degree of reaction at tip\n",
+      "\n",
+      "#output\n",
+      "print '(a)for hub\\n    (1)Inlet angle of the nozzle blade at hub height is %3.1f degree\\n    (2)Inlet angle of the rotor blade at hub is %3i degree\\n    (3)Outlet angle of the rotor blade at hub is %3.2f degree\\n    (4)Degree of reaction at hub is %0.2f %%\\n(b)for tip\\n    (1)Inlet angle of the nozzle blade at tip height is %3.2f degree\\n    (2)Inlet angle of the rotor blade at tip is %3i degree\\n    (3)Outlet angle of the rotor blade at tip is %3i degree\\n    (4)Degree of reaction at tip is %0.2f'%(a1h,b1h,b2h,Rh*100,a1t,b1t,b2t,Rt*100)\n",
+      "# Answer for degree of reaction is not correct in the textbook."
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)for hub\n",
+        "    (1)Inlet angle of the nozzle blade at hub height is 79.4 degree\n",
+        "    (2)Inlet angle of the rotor blade at hub is  72 degree\n",
+        "    (3)Outlet angle of the rotor blade at hub is 72.75 degree\n",
+        "    (4)Degree of reaction at hub is 2.93 %\n",
+        "(b)for tip\n",
+        "    (1)Inlet angle of the nozzle blade at tip height is 72.69 degree\n",
+        "    (2)Inlet angle of the rotor blade at tip is -29 degree\n",
+        "    (3)Outlet angle of the rotor blade at tip is  77 degree\n",
+        "    (4)Degree of reaction at tip is 65.04\n"
+       ]
+      }
+     ],
+     "prompt_number": 12
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 5.8 Page 228"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "Ca=180#Air velocity at the exit of nozzle in m/s\n",
+      "a1=(90-27)#Nozzle inclination perpendicular to direction of rotation in degree\n",
+      "R=0.5#Degree of reaction\n",
+      "U=180#Blade speed in m/s\n",
+      "\n",
+      "#calculations\n",
+      "Cx1=Ca*tan(a1*pi/180)#Inlet whirl velocity in m/s\n",
+      "b11=degrees(atan((Cx1-U)/Ca))#Inlet angle of the rotor blade at inlet velocity triangle in degree\n",
+      "pi=Ca/U#Ratio of air velocity and blade velocity \n",
+      "b21=degrees(atan((2*R/pi))+tan(b11*pi/180))#Outlet angle of the rotor blade at inlet velocity triangle in degree\n",
+      "C2=Ca#Exit velocity of the steam in m/s\n",
+      "b22=degrees(atan(U/C2))#Outlet angle of the rotor blade at outlet velocity triangle in degree\n",
+      "b12=b11#Inlet angle of the rotor blade at outlet velocity triangle in degree as np change in rotor inlet conditions \n",
+      "R=(pi*(tan(b22*pi/180)-tan(b12*pi/180)))/2#Degree of reaction \n",
+      "#output\n",
+      "print '(a)blade angles\\n    Inlet angle of the rotor blade at inlet velocity triangle is %3.1f degree\\n    Outlet angle of the rotor blade at inlet velocity triangle is %3.f degree\\n(b)Degree of reaction is %3.4f\\n(c)Inlet angle of the rotor blade at outlet velocity triangle is %3.f degree\\n(d)Outlet angle of the rotor blade at outlet velocity triangle is %3.1f degree'%(b11,b21,R,b22,b12)\n",
+      "# Answer in the textbook is not correct for some part."
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)blade angles\n",
+        "    Inlet angle of the rotor blade at inlet velocity triangle is 43.9 degree\n",
+        "    Outlet angle of the rotor blade at inlet velocity triangle is  59 degree\n",
+        "(b)Degree of reaction is 0.0032\n",
+        "(c)Inlet angle of the rotor blade at outlet velocity triangle is  45 degree\n",
+        "(d)Outlet angle of the rotor blade at outlet velocity triangle is 43.9 degree\n"
+       ]
+      }
+     ],
+     "prompt_number": 13
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 5.9 Page 229"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import cos\n",
+      "#input data\n",
+      "U=300#Blade speed of turbine in m/s\n",
+      "m=2.5#Mass flow rate in kg/s\n",
+      "T0=773#Gas temperature at turbine inlet in K\n",
+      "T2=573#Gaas temperature at turbine outlet in K\n",
+      "a1=70#Fixed blade outlet angle in degree\n",
+      "Ca=200#Axial velocity in m/s\n",
+      "Cp=1.005#Specific heat of gas at constant pressure in kJ/kg.K\n",
+      "#calculations\n",
+      "W=m*Cp*(T0-T2)#Power developed by turbine in kW\n",
+      "Wm=Cp*(T0-T2)#Stage work done per unit mass flow rate in kJ/kg\n",
+      "Wx1Wx2=Wm*10**3/U#Sum of whirl components of velocity at inlet and outlet in m/s\n",
+      "Wx1=(Ca*tan(a1*pi/180))-U#Inlet whirl velocity in m/s\n",
+      "Wx2=Wx1Wx2-Wx1#Outlet whirl velocity in m/s\n",
+      "R=(Wx2-Wx1)/(2*U)#Degree of reaction\n",
+      "Wx2Wx1=Wm*10**3*R#Energy input due to whirl component velocity in (m/s)**2\n",
+      "C1=Ca/cos(a1*pi/180)#Velocity of steam at exit from nozzle in m/s \n",
+      "nb=(Wm*10**3)/(((C1**2)/2)+Wx2Wx1)#Blade efficiency\n",
+      "\n",
+      "#output\n",
+      "print '(a)Power developed by turbine is %3.1f kW\\n(b)Degree of reaction is %0.2f %%\\n(c)Blade efficiency is %0.2f %%\\n'%(W,R*100,nb*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Power developed by turbine is 502.5 kW\n",
+        "(b)Degree of reaction is 184.35 %\n",
+        "(c)Blade efficiency is 51.03 %\n",
+        "\n"
+       ]
+      }
+     ],
+     "prompt_number": 14
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 5.10 Page 230"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from __future__ import division\n",
+      "#input data\n",
+      "R=0.5#Degree of reaction\n",
+      "P0=2.2#Inlet pressure in bar\n",
+      "T0=443#Inlet temperature in K\n",
+      "N=2400#Rotor running speed in rpm\n",
+      "Dm=0.5#Rotor mean diameter in m\n",
+      "a1=36#Rotor inlet angle in degree\n",
+      "a2=19#Stator exit angle in degree\n",
+      "ns=0.88#Stage efficiency\n",
+      "m=1#Mass flow rate of steam in kg/s\n",
+      "\n",
+      "#calculations\n",
+      "b2=a1#Outlet angle of the rotor blade in degree\n",
+      "b1=a2#Inlet angle of the rotor blade in degree\n",
+      "U=(3.1415*Dm*N)/60#Mean blade speed in m/s\n",
+      "Ca=(2*U*R)/(tan(b2*pi/180)-tan(b1*pi/180))#Axial velocity in m/s\n",
+      "W=m*U*Ca*(tan(a1*pi/180)+tan(a2*pi/180))*10**-3#Power output in kW\n",
+      "dh=W/ns#Stage enthalpy drop in kJ/kg\n",
+      "\n",
+      "#output\n",
+      "print '(a)Power output is %3.2f kW\\n(b)Stage enthalpy drop is %3.2f kJ/kg'%(W,dh)\n",
+      "# Answer in the textbook is not correct."
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Power output is 12.59 kW\n",
+        "(b)Stage enthalpy drop is 14.31 kJ/kg\n"
+       ]
+      }
+     ],
+     "prompt_number": 15
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 5.11 Page 231"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from __future__ import division\n",
+      "#input data\n",
+      "P0=800#Inlet pressure of hot gas in kPa\n",
+      "T1=973#Inlet temperature of hot gas in K\n",
+      "P2=100#Final pressure of hot gas in kPa\n",
+      "a1=73#Nozzle angle in degree\n",
+      "m=35#Mass flow rate in kg/s\n",
+      "ns=0.9#Nozzle efficiency\n",
+      "Cp=1.005#Specific heat of gas at constant pressure in kJ/kg.K\n",
+      "r=1.4#Ratio of specific heats of air\n",
+      "\n",
+      "#calculations\n",
+      "b1=degrees(atan(tan(a1*pi/180)/2))#Inlet angle of the rotor blade in degree\n",
+      "b2=b1#Outlet angle of the rotor blade in degree\n",
+      "pi=2/tan(a1*pi/180)#Flow coefficient\n",
+      "psil=pi*(tan(b1*pi/180)+tan(b2*pi/180))#Blade loading coefficient\n",
+      "dh=ns*Cp*T1*(1-(P2/P0)**((r-1)/r))#Change in enthalpy in kJ/kg\n",
+      "W=m*dh*10**-3#Power developed in MW\n",
+      "\n",
+      "#output\n",
+      "print '(a)Rotor blade angles\\n    Inlet angle of the rotor blade is %3.2f degree\\n    Outlet angle of the rotor blade is %3.2f degree\\n(b)Flow coefficient is %3.3f\\n(c)Blade loading coefficient is %3.f\\n(d)Power developed is %3.1f MW'%(b1,b2,pi,psil,W)\n",
+      "# Answer in the textbook is not accurate."
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Rotor blade angles\n",
+        "    Inlet angle of the rotor blade is 12.12 degree\n",
+        "    Outlet angle of the rotor blade is 12.12 degree\n",
+        "(b)Flow coefficient is 4.658\n",
+        "(c)Blade loading coefficient is   3\n",
+        "(d)Power developed is 13.8 MW\n"
+       ]
+      }
+     ],
+     "prompt_number": 16
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 5.12 Page 233"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import sin, pi\n",
+      "#Ex Page\n",
+      "#input data\n",
+      "P0=100#Initial pressure of steam in bar\n",
+      "T0=773#Initial temperature of steam in K\n",
+      "D=1#Turbine diameter in m\n",
+      "N=3000#Speed of turbine in rpm\n",
+      "m=100#Mass flow rate of steam in kg/s\n",
+      "a1=70#Exit angle of the first stage nozzle in degree\n",
+      "ns1=0.78#Stage efficiency of first stage \n",
+      "ns2=ns1#Stage efficiency of second stage\n",
+      "\n",
+      "#calculations\n",
+      "U=(pi*D*N)/60#Mean blade speed in m/s\n",
+      "C1=(2*U)/sin(a1*pi/180)#Velocity of steam at exit from nozzle in m/s \n",
+      "b11=degrees(atan(tan(a1*pi/180)/2))#Inlet angle of the rotor blade in degree\n",
+      "b21=b11#Outlet angle of the rotor blade in degree\n",
+      "b12=b21#Inlet angle of the rotor blade in second stage in degree\n",
+      "b22=b12#Outlet angle of the rotor blade in second stage in degree\n",
+      "W=4*m*U**2*10**-6#Total work done in both the stages in MW\n",
+      "dh02=2*U**2*10**-3#Change in enthalpy in first stage of turbine in kJ/kg\n",
+      "dh02s=(dh02/ns1)#Change in enthalpy isentropically of turine first stage in kJ/kg\n",
+      "print 'The values of enthalpy and specific volume are taken from the mollier chart at inlet and exit conditions respectively'\n",
+      "h0=3370#Enthalpy at beginning of first stage in kJ/kg\n",
+      "h2=h0-dh02#Enthalpy at the end of first stage in kJ/kg\n",
+      "h2s=h0-dh02s#Isentropic enthalpy at the end of first stage in kJ/kg\n",
+      "v2=0.041#Specific volume at the end of first stage in m**3/kg\n",
+      "dh24=2*U**2*10**-3#Change in enthalpy in second stage of turbine in kJ/kg\n",
+      "dh24s=dh24/ns2#Change in enthalpy isentropically of turine second stage in kJ/kg\n",
+      "h4=h2-dh24#Enthalpy at beginning of second stage in kJ/kg\n",
+      "h4s=h2-dh24s#Isentropic enthalpy at the end of second stage in kJ/kg\n",
+      "v4=0.05#Specific volume at the end of second stage in m**3/kg\n",
+      "\n",
+      "Ca=C1*cos(a1*pi/180)#Axial velocity in m/s\n",
+      "h1r=(m*v2)/(3.1415*D*Ca)#Blade height at first stage rotor exit in m\n",
+      "h2r=(m*v4)/(3.1415*D*Ca)#Blade height at second stage rotor exit in m\n",
+      "\n",
+      "#output\n",
+      "print '\\n\\n(a)rotor blade angles\\n    Inlet angle of the rotor blade is %3.2f degree\\n    Outlet angle of the rotor blade is %3.2f degree\\n    Inlet angle of the rotor blade in second stage is %3.2f degres\\n    Outlet angle of the rotor blade in second stage is %3.2f degree\\n(b)Total work done or Power developed in both the stages is %3.2f MW\\n(c)final state of steam\\n    Enthalpy at beginning of first stage is %3i kJ/kg\\n    Enthalpy at the end of first stage is %3.2f kJ/kg\\n    Isentropic enthalpy at the end of first stage is %3.2f kJ/kg\\n    Specific volume at the end of first stage is %3.3f m**3/kg\\n    Enthalpy at beginning of second stage is %3.1f kJ/kg\\n    Isentropic enthalpy at the end of second stage is %3.2f kJ/kg\\n    Specific volume at the end of second stage is %3.2f m**3/kg\\n(d)blade height\\n    Blade height at first stage rotor exit is %3.4f m\\n    Blade height at second stage rotor exit is %3.4f m'%(b11,b21,b12,b22,W,h0,h2,h2s,v2,h4,h4s,v4,h1r,h2r)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "The values of enthalpy and specific volume are taken from the mollier chart at inlet and exit conditions respectively\n",
+        "\n",
+        "\n",
+        "(a)rotor blade angles\n",
+        "    Inlet angle of the rotor blade is 53.95 degree\n",
+        "    Outlet angle of the rotor blade is 53.95 degree\n",
+        "    Inlet angle of the rotor blade in second stage is 53.95 degres\n",
+        "    Outlet angle of the rotor blade in second stage is 53.95 degree\n",
+        "(b)Total work done or Power developed in both the stages is 9.87 MW\n",
+        "(c)final state of steam\n",
+        "    Enthalpy at beginning of first stage is 3370 kJ/kg\n",
+        "    Enthalpy at the end of first stage is 3320.65 kJ/kg\n",
+        "    Isentropic enthalpy at the end of first stage is 3306.73 kJ/kg\n",
+        "    Specific volume at the end of first stage is 0.041 m**3/kg\n",
+        "    Enthalpy at beginning of second stage is 3271.3 kJ/kg\n",
+        "    Isentropic enthalpy at the end of second stage is 3257.39 kJ/kg\n",
+        "    Specific volume at the end of second stage is 0.05 m**3/kg\n",
+        "(d)blade height\n",
+        "    Blade height at first stage rotor exit is 0.0114 m\n",
+        "    Blade height at second stage rotor exit is 0.0139 m\n"
+       ]
+      }
+     ],
+     "prompt_number": 17
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 5.13 Page 236"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "P0=100#Initial pressure of steam in bar\n",
+      "T0=773#Initial temperature of steam in K\n",
+      "D=1#Turbine diameter in m\n",
+      "N=3000#Speed of turbine in rpm\n",
+      "m=100#Mass flow rate of steam in kg/s\n",
+      "a1=70#Exit angle of the first stage nozzle in degree\n",
+      "ns=0.65#Stage efficiency of first stage \n",
+      "\n",
+      "#calculations\n",
+      "U=(3.1415*D*N)/60#Mean blade speed in m/s\n",
+      "C1=(4*U)/sin(a1*pi/180)#Velocity of steam at exit from nozzle in m/s\n",
+      "Ca=C1*cos(a1*pi/180)#Axial velocity in m/s\n",
+      "Wx1=3*U#Inlet whirl velocity in m/s\n",
+      "b11=degrees(atan(Wx1/Ca))#Inlet angle of the rotor blade in degree\n",
+      "b21=b11#Outlet angle of the rotor blade in degree\n",
+      "C2=Ca#Velocity of steam at exit from stage in m/s\n",
+      "b22=degrees(atan(U/Ca))#Outlet angle of the rotor blade  in degree\n",
+      "b12=b22#Inlet angle of the rotor blade in  in degree\n",
+      "W=m*8*U**2*10**-6#Total work done or power developed in MW\n",
+      "print 'The values of enthalpy and specific volume are taken from the mollier chart at inlet and exit conditions respectively'\n",
+      "h0=3370#Enthalpy at beginning of  stage in kJ/kg\n",
+      "dh04=(W*10**3)/m#Change in enthalpy  of turbine in kJ/kg\n",
+      "dh04s=dh04/ns#Change in enthalpy isentropically of turine  in kJ/kg\n",
+      "h4=h0-dh04#Enthalpy at beginning of stage in kJ/kg\n",
+      "h4s=h0-dh04s#Isentropic enthalpy at the end of  stage in kJ/kg\n",
+      "v4=0.105#Specific volume at the end of stage in m**3/kg\n",
+      "h=(m*v4)/(3.1415*D*Ca)#Rotor blade height in m\n",
+      "\n",
+      "print '\\n\\n(a)rotor blade angles\\n    Inlet angle of the rotor blade is %3.2f degree\\n    Outlet angle of the rotor blade is %3.2f degree\\n    Inlet angle of the rotor blade in second stage is %3.2f degres\\n    Outlet angle of the rotor blade in second stage is %3.2f degree\\n(b)Total work done or Power developed in both the stages is %3.2f MW\\n(c)final state of steam\\n    Enthalpy at beginning of first stage is %3i kJ/kg\\n    Enthalpy at beginning of stage is %3.1f kJ/kg\\n    Isentropic enthalpy at the end of stage is %3.2f kJ/kg\\n    Specific volume at the end of stage is %3.3f m**3/kg\\n(d)rotor blade height is %3.4f m'%(b11,b21,b12,b22,W,h0,h4,h4s,v4,h)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "The values of enthalpy and specific volume are taken from the mollier chart at inlet and exit conditions respectively\n",
+        "\n",
+        "\n",
+        "(a)rotor blade angles\n",
+        "    Inlet angle of the rotor blade is 64.11 degree\n",
+        "    Outlet angle of the rotor blade is 64.11 degree\n",
+        "    Inlet angle of the rotor blade in second stage is 34.48 degres\n",
+        "    Outlet angle of the rotor blade in second stage is 34.48 degree\n",
+        "(b)Total work done or Power developed in both the stages is 19.74 MW\n",
+        "(c)final state of steam\n",
+        "    Enthalpy at beginning of first stage is 3370 kJ/kg\n",
+        "    Enthalpy at beginning of stage is 3172.6 kJ/kg\n",
+        "    Isentropic enthalpy at the end of stage is 3066.34 kJ/kg\n",
+        "    Specific volume at the end of stage is 0.105 m**3/kg\n",
+        "(d)rotor blade height is 0.0146 m\n"
+       ]
+      }
+     ],
+     "prompt_number": 18
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 5.14 Page 238"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "a1=(90-30)#Nozzle angle in axial direction in degree\n",
+      "Ca=180#Axial velocity in m/s\n",
+      "U=280#Rotor blade speed in m/s\n",
+      "R=0.25#Degree of reaction\n",
+      "\n",
+      "#calculations\n",
+      "Cx1=Ca*tan(a1*pi/180)#Velocity of whirl at inlet in m/s\n",
+      "b1=degrees(atan((Cx1-U)/Ca))#Blade angle at inlet in degree\n",
+      "b2=a1#Blade angle at exit in degree as degree of reaction is 0.5\n",
+      "\n",
+      "#output\n",
+      "print '(a)Blade angle at inlet is %3i degree\\n(b)Blade angle at exit is %3i degree'%(b1,b2)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Blade angle at inlet is  10 degree\n",
+        "(b)Blade angle at exit is  60 degree\n"
+       ]
+      }
+     ],
+     "prompt_number": 19
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 5.15 Page 239"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "R=0.5#Degree of reaction\n",
+      "ns=0.85#Stage efficiency\n",
+      "P0=800#Inlet pressure of hot gas in kPa\n",
+      "T0=900#Inlet temperature of hot gas in K\n",
+      "U=160#Blade speed in m/s\n",
+      "m=75#Mass flow rate of hot gas in kg/s\n",
+      "a1=70#Absolute air angle at first stage nozzle exit in degree\n",
+      "\n",
+      "#calculations\n",
+      "C1=U/sin(a1*pi/180)#Velocity of steam at exit from nozzle in m/s\n",
+      "Ca=C1*cos(a1*pi/180)#Axial velocity of hot gas in m/s\n",
+      "C2=Ca#Velocity of steam at exit from stage in m/s\n",
+      "b1=0#Blade angle at inlet in degree as Wx1=0 \n",
+      "a2=b1#Stator exit angle in degree as degree of reaction is 0.5\n",
+      "b2=a1#Blade angle at outlet in degree as degree of reaction is 0.5\n",
+      "Cx2=0#Velocity of whirl at outlet in m/s\n",
+      "Cx1=U#Velocity of whirl at inlet in m/s\n",
+      "W=m*U*(Cx1+Cx2)*10**-6#Power developed in MW\n",
+      "Wm=W*10**3/m#Work done per unit mass flow rate in kJ/kg\n",
+      "dhs=Wm/ns#Isentropic enthalpy drop in kJ/kg\n",
+      "\n",
+      "#output\n",
+      "print '(a)Rotor blade angles\\n    Absolute air angle at first stage nozzle exit is %3i degree\\n    Blade angle at outlet is %3i degree\\n    Blade angle at inlet is %3i degree\\n    Stator exit angle is %3i degree\\n(b)Power developed is %3.2f MW\\n(c)Isentropic enthalpy drop is %3.2f kJ/kg'%(a1,b2,b1,a2,W,dhs)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Rotor blade angles\n",
+        "    Absolute air angle at first stage nozzle exit is  70 degree\n",
+        "    Blade angle at outlet is  70 degree\n",
+        "    Blade angle at inlet is   0 degree\n",
+        "    Stator exit angle is   0 degree\n",
+        "(b)Power developed is 1.92 MW\n",
+        "(c)Isentropic enthalpy drop is 30.12 kJ/kg\n"
+       ]
+      }
+     ],
+     "prompt_number": 20
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 5.16 Page 240"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from __future__ import division\n",
+      "from math import pi\n",
+      "#input data\n",
+      "b1m=46#Rotor blade angle at entry at mean section in degree\n",
+      "b2m=75#Rotor blade angle at exit at mean section in degree\n",
+      "a1m=75#Nozzle angle at exit at mean section in degree\n",
+      "DhDt=0.6#Hub to tip ratio\n",
+      "N=7500#Mean rotor speed in rpm\n",
+      "Dh=0.45#Hub diameter in m\n",
+      "\n",
+      "#calculations\n",
+      "R=0.5#Degree of reaction as a1m=b2m\n",
+      "a2m=b1m#Stator angle at exit at mean section in degree\n",
+      "Dm=(Dh+(Dh/DhDt))/2#Mean diameter of turbine at mean section in m\n",
+      "Um=(pi*DhDt*N)/60#Mean blade speed in m/s\n",
+      "Ca=Um/(tan(a1m*pi/180)-tan(b1m*pi/180))#Axial velocity in m/s\n",
+      "fi=Ca/Um#Flow coefficient\n",
+      "psil=fi*(tan(b1m*pi/180)+tan(b2m*pi/180))#Blade loading coefficient\n",
+      "a1h=degrees(atan(tan(a1m*pi/180)*((Dm/2)/(Dh/2))))#Nozzle angle at inlet at root section in degree\n",
+      "Uh=(3.14*Dh*N)/60#Blade speed at root section in m/s\n",
+      "b1h=degrees(atan(tan(a1h*pi/180)-(Uh/Ca)))#Rotor blade angle at entry at root section in degree\n",
+      "a2h=degrees(atan(tan(a2m*pi/180)*((Dm/2)/(Dh/2))))#Stator angle at exit at root section in degree\n",
+      "b2h=degrees(atan((Uh/Ca)+tan(a2h*pi/180)))#Rotor blade angle at exit at root section in degree\n",
+      "pih=Ca/Uh#Flow coefficient at root section\n",
+      "Rh=(pih/2)*(tan(b2h*pi/180)-tan(b1h*pi/180))#Degree of reaction at root section\n",
+      "psilh=pih*(tan(b1h*pi/180)+tan(b2h*pi/180))#Blade loading coefficient at root section\n",
+      "\n",
+      "#output\n",
+      "print 'Mean section\\n    (a)Degree of reaction is %3.1f\\n    (b)Blade loading coefficient is %3.2f\\nRoot section    (a)Degree of reaction is %3.2f\\n    (b)Blade loading coefficient is %3.2f'%(R,psil,Rh,psilh)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "Mean section\n",
+        "    (a)Degree of reaction is 0.5\n",
+        "    (b)Blade loading coefficient is 1.77\n",
+        "Root section    (a)Degree of reaction is 0.11\n",
+        "    (b)Blade loading coefficient is 3.14\n"
+       ]
+      }
+     ],
+     "prompt_number": 21
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 5.17 Page 242"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "T00=973#Total head inlet temperature in K\n",
+      "P00=4.5#Total head inlet pressure in bar\n",
+      "P2=1.6#Static head outlet pressure in bar\n",
+      "m=20#Gas flow rate in kg/s\n",
+      "a1=(90-28)#Nozzle outlet angle measured perpendicular to blade velocity in degree\n",
+      "Dmh=10#Mean blade diameter to blade height ratio \n",
+      "NLC=0.1#Nozzle loss coefficient\n",
+      "Cp=1155.6#Specific heat of gas at a constant pressure in kJ/kg\n",
+      "R=289#Gas constant in J/kg\n",
+      "r=1.333#Ratio of specific heats of gas \n",
+      "\n",
+      "#calculations\n",
+      "T2ss=T00*(P2/P00)**((r-1)/r)#Isentropic temperature at outlet in mid section in K here T00=T01\n",
+      "T1s=T2ss#Isentropic temperature at inlet at mid section in K\n",
+      "C1m=(2*Cp*(T00-T1s)/1.1)**(1/2)#Velocity of steam at exit from nozzle at mid section in m/s\n",
+      "T1=T00-((C1m**2)/(2*Cp))#Gas temperature at mid section in K\n",
+      "d=(P2*10**5)/(R*T1)#Density of gas in kg/m**3\n",
+      "Rg=(Cp*(r-1)/r)#Gas constant of the gas in kJ/kg\n",
+      "Ca=C1m*cos(a1*pi/180)#Axial velocity in m/s\n",
+      "h=((m/(d*Ca))*(1/(Dmh*3.1415)))**(1/2)#Hub height in m\n",
+      "Dm=Dmh*h#Mean blade diameter in m\n",
+      "Dh=Dm-h#Hub diameter in m\n",
+      "a1h=degrees(atan(((Dm/2)/(Dh/2))*tan(a1*pi/180)))#Discharge angle at hub in degree\n",
+      "C1h=Ca/cos(a1h*pi/180)#Gas velocity at hub section in m/s\n",
+      "T1h=T00-((C1h**2)/(2*Cp))#Gas temperature at hub in K here T01=T00\n",
+      "Dt=Dm+h#Tip diameter in m\n",
+      "a1t=degrees(atan(((Dm/2)/(Dt/2))*tan(a1*pi/180)))#Gas discharge angle at tip in degree\n",
+      "C1t=Ca/cos(a1t)#Gas velocity at tip in m/s\n",
+      "T1t=T00-((C1t**2)/(2*Cp))#Gas temperature in K here T00=T01\n",
+      "\n",
+      "#output\n",
+      "print '(a)At mid section\\n    Gas velocity is %3.1f m/s\\n    Gas temperature is %3.1f K\\n    Gas discharge angle is %3i degree\\n(b)At hub section\\n    Gas velocity is %3.1f m/s\\n    Gas temperature is %3.2f K\\n    Gas discharge angle is %3.2f degree\\n(c)At tip section\\n    Gas velocity is %3.1f m/s\\n    Gas temperature is %3.2f K\\n    Gas discharge angle is %3.2f degree'%(C1m,T1,a1,C1h,T1h,a1h,C1t,T1t,a1t)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)At mid section\n",
+        "    Gas velocity is 682.2 m/s\n",
+        "    Gas temperature is 771.6 K\n",
+        "    Gas discharge angle is  62 degree\n",
+        "(b)At hub section\n",
+        "    Gas velocity is 742.0 m/s\n",
+        "    Gas temperature is 734.80 K\n",
+        "    Gas discharge angle is 64.43 degree\n",
+        "(c)At tip section\n",
+        "    Gas velocity is -320.3 m/s\n",
+        "    Gas temperature is 928.61 K\n",
+        "    Gas discharge angle is 59.68 degree\n"
+       ]
+      }
+     ],
+     "prompt_number": 22
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 5.18 Page 244"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import sin, cos, atan, tan, pi, degrees\n",
+      "#input data\n",
+      "a1=75#Nozzle air angle in degree\n",
+      "Rh=0#Degree of reaction\n",
+      "N=6000#Running speed of hub in rpm\n",
+      "Dh=0.45#Hub diameter in m\n",
+      "Df=0.75#Tip diameter in m\n",
+      "\n",
+      "\n",
+      "#calculations\n",
+      "Uh=(3.1415*Dh*N)/60#Hub speed in m/s\n",
+      "C1h=Uh/((sin(a1*pi/180))/2)#Velocity of steam at exit from nozzle in hub in m/s\n",
+      "Cah=C1h*cos(a1*pi/180)#Axial velocity at hub in m/s\n",
+      "Cx1h=C1h*sin(a1*pi/180)#Whirl component of velocity at inlet in hub in m/s\n",
+      "b1h=degrees(atan((Cx1h-Uh)/Cah))#Rotor blade angle at entry at hub section in degree\n",
+      "b2h=b1h#Rotor blade angle at exit at mean section in degree as zero reaction section\n",
+      "sopt=sin(a1*pi/180)/2#Blade to gas speed ratio at hub\n",
+      "rm=((Dh/2)+(Df/2))/2#Mean radius in m\n",
+      "rmrh=(rm/(Dh/2))**((sin(a1*pi/180))**2)#Ratio of inlet velocity at hub and mean for constant nozzle air angle at hub section\n",
+      "C1m=C1h/rmrh#Velocity of steam at exit from nozzle at mean section in m/s\n",
+      "Cx1m=Cx1h/rmrh#Velocity of whirl at inlet at mean section in m/s\n",
+      "Ca1m=Cah/rmrh#Axial velocity at mean section in m/s\n",
+      "Um=(3.1415*2*rm*N)/60#Mean blade speed in m/s\n",
+      "b1m=degrees(atan((Cx1m-Um)/Ca1m))#Rotor blade angle at entry at mean section in degree\n",
+      "b2m=degrees(atan(Um/Ca1m))#Rotor blade angle at exit at mean section in degree for axial exit Cx2=0\n",
+      "s=Um/C1m#Blade to gas ratio at mean\n",
+      "Rm=(Ca1m/(2*Um))*(tan(b2m*pi/180)-tan(b1m*pi/180))#Degree of reaction of mean section\n",
+      "rmrt=((rm)/(Df/2))**((sin(a1*pi/180))**2)#Ratio of inlet velocity at tip and mean for constant nozzle air angle at tip section\n",
+      "C1t=C1m*rmrt#Velocity of steam at exit from nozzle at tip section in m/s\n",
+      "Cx1t=Cx1m*rmrt#Velocity of whirl at inlet at tip section in m/s\n",
+      "Ca1t=Ca1m*rmrt#Axial velocity at tip section in m/s\n",
+      "Ut=(3.1415*Df*N)/60#Mean tip speed in m/s\n",
+      "b1t=degrees(atan((Cx1t-Ut)/Ca1t))#Rotor blade angle at entry at tip section in degree\n",
+      "b2t=degrees(atan(Ut/Ca1t))#Rotor blade angle at exit at tip section in degree for axial exit Cx2=0\n",
+      "st=Ut/C1t#Blade to gas ratio at tip\n",
+      "Rf=(Ca1t/(2*Ut))*(tan(b2t*pi/180)-tan(b1t*pi/180))#Degree of reaction of tip section\n",
+      "\n",
+      "#output\n",
+      "print '(1)Hub section\\n    (a)\\n         Absolute air angle is %3.2f degree\\n         Relative air angle is %3.2f degree\\n    (b)Blade to gas speed ratio is %3.3f\\n    (c)Degree of reaction is %3i\\n(2)Mean section\\n    (a)\\n         Absolute air angle is %3.2f degree\\n         Relative air angle is %3.2f degree\\n    (b)Blade to gas speed ratio is %3.3f\\n    (c)Degree of reaction is %3.3f\\n(3)Tip section\\n    (a)\\n         Absolute air angle is %3.2f degree\\n         Relative air angle is %3.2f degree\\n    (b)Blade to gas speed ratio is %3.3f\\n    (c)Degree of reaction is %3.3f\\n'%(b1h,b2h,sopt,Rh,b1m,b2m,s,Rm,b1t,b2t,st,Rf)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(1)Hub section\n",
+        "    (a)\n",
+        "         Absolute air angle is 61.81 degree\n",
+        "         Relative air angle is 61.81 degree\n",
+        "    (b)Blade to gas speed ratio is 0.483\n",
+        "    (c)Degree of reaction is   0\n",
+        "(2)Mean section\n",
+        "    (a)\n",
+        "         Absolute air angle is 25.55 degree\n",
+        "         Relative air angle is 72.92 degree\n",
+        "    (b)Blade to gas speed ratio is 0.842\n",
+        "    (c)Degree of reaction is 0.427\n",
+        "(3)Tip section\n",
+        "    (a)\n",
+        "         Absolute air angle is -51.94 degree\n",
+        "         Relative air angle is 78.71 degree\n",
+        "    (b)Blade to gas speed ratio is 1.296\n",
+        "    (c)Degree of reaction is 0.627\n",
+        "\n"
+       ]
+      }
+     ],
+     "prompt_number": 23
+    }
+   ],
+   "metadata": {}
+  }
+ ]
+}
\ No newline at end of file
diff --git a/Turbomachines_by_A._V._Arasu/Ch6.ipynb b/Turbomachines_by_A._V._Arasu/Ch6.ipynb
new file mode 100644
index 00000000..44de0471
--- /dev/null
+++ b/Turbomachines_by_A._V._Arasu/Ch6.ipynb
@@ -0,0 +1,442 @@
+{
+ "metadata": {
+  "name": "",
+  "signature": "sha256:aae7358a1641809b7b2e92e647a38df4d3df23fcb8fc4fc8de6985e2dc22bd13"
+ },
+ "nbformat": 3,
+ "nbformat_minor": 0,
+ "worksheets": [
+  {
+   "cells": [
+    {
+     "cell_type": "heading",
+     "level": 1,
+     "metadata": {},
+     "source": [
+      "Chapter 6 - Radial Flow Gas and Steam Turbines"
+     ]
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 6.1 Page 266"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from __future__ import division\n",
+      "from math import atan, pi, tan, degrees, cos\n",
+      "#input data\n",
+      "P00=3#The pressure at which air is received in bar\n",
+      "T00=373#The temperature at which air is received in K\n",
+      "rt=0.5#The rotor tip diameter of turbine in m\n",
+      "rh=0.3#The rotor exit diameter of the turbine in m\n",
+      "b=0.03#The rotor blade width at entry in m\n",
+      "b11=60#The air angle at rotor entry in degree\n",
+      "a11=25#The air angle at nozzle exit in degree\n",
+      "Ps=2#The stage pressure ratio\n",
+      "nn=0.97#The nozzle efficiency\n",
+      "N=7200#The speed of the turbine rotation 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",
+      "U1=(3.14*rt*N)/60#Peripheral velocity of impeller at inlet in m/s\n",
+      "Cr=U1/(1/tan(pi/180*a11)-1/tan(pi/180*b11))#The radial velocity at inlet in m/s\n",
+      "ps1=Cr/U1#Flow coefficient \n",
+      "sl=1+(ps1*1/tan(pi/180*b11))#Loading coefficient\n",
+      "DR=((1-(ps1*1/tan(pi/180*b11)))/2)#Degree of reaction\n",
+      "nts=((sl*U1**2)/(Cp*T00*(1-((1/Ps)**((r-1)/r)))))#Stage efficiency of the turbine\n",
+      "C2=Cr#Absolute velocity at the exit in m/s\n",
+      "U2=(3.1415*rh*N)/60#Peripheral velocity of impeller at exit in m/s\n",
+      "b22=degrees(atan(C2/U2))#The air angle at rotor exit in degree\n",
+      "dT=DR*U1*Cr*1/tan(pi/180*a11)/Cp#Total actual change in temperature in a stage turbine in K\n",
+      "dT0=(U1*Cr*1/tan(pi/180*a11))/Cp#The total change in temperature in turbine in K\n",
+      "T02=T00-dT0#The exit absolute temperature in K\n",
+      "T2=T02-((C2**2)/(2*Cp))#The actual exit temperature in K\n",
+      "T1=dT+T2#The actual inlet temperature in K\n",
+      "Cx1=Cr*1/tan(pi/180*a11)#Inlet absolute velocity of air in tangential direction in m/s\n",
+      "C1=Cx1/cos(pi/180*a11)#Absolute velocity at the inlet in m/s\n",
+      "dT1=(C1**2/2)/(Cp*nn)#The absolute change in temperature at the first stage in K\n",
+      "dP1=(1-(dT1/T00))**(r/(r-1))#The absolute pressure ratio in first stage \n",
+      "P1=dP1*P00#The inlet pressure in bar\n",
+      "d1=(P1*10**5)/(R*T1)#The inlet density in kg/m**3\n",
+      "A1=3.1415*rt*b#The inlet area of the turbine in m**2\n",
+      "m=d1*A1*Cr#The mass flow rate of air at inlet in kg/s\n",
+      "P2=P00/Ps#The exit pressure in bar\n",
+      "d2=(P2*10**5)/(R*T2)#The exit density of air in kg/m**3\n",
+      "bh=(m/(d2*3.1415*rh*Cr))#Rotor width at the exit in m\n",
+      "W=m*U1*Cx1*10**-3#The power developed by the turbine in kW\n",
+      "\n",
+      "#output\n",
+      "print '(a)\\n    (1)The flow coefficient is %3.3f\\n    (2)The loading coefficient is %3.3f\\n(b)\\n    (1)The degree of reaction is %0.2f %% \\n    (2)The stage efficiency of the turbine is %0.2f %% \\n(c)\\n    (1)The air angle at the rotor exit is %3.2f degree\\n    (2)The width at the rotor exit is %0.2f cm\\n(d)\\n    (1)The mass flow rate is %3.2f kg/s\\n    (2)The power developed is %3.2f kW'%(ps1,sl,DR*100,nts*100,b22,bh*100,m,W)\n",
+      "# answer in the textbook is not correct."
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)\n",
+        "    (1)The flow coefficient is 0.638\n",
+        "    (2)The loading coefficient is 1.368\n",
+        "(b)\n",
+        "    (1)The degree of reaction is 31.58 % \n",
+        "    (2)The stage efficiency of the turbine is 72.12 % \n",
+        "(c)\n",
+        "    (1)The air angle at the rotor exit is 46.75 degree\n",
+        "    (2)The width at the rotor exit is 6.31 cm\n",
+        "(d)\n",
+        "    (1)The mass flow rate is 11.78 kg/s\n",
+        "    (2)The power developed is 572.01 kW\n"
+       ]
+      }
+     ],
+     "prompt_number": 1
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 6.2 Page 270"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import sin\n",
+      "#input data\n",
+      "P0=4#Overall stage pressure ratio \n",
+      "T00=557#Temperature at entry in K\n",
+      "P3=1#Diffuser exit pressure in bar\n",
+      "m=6.5#Mass flow rate of air in kg/s\n",
+      "ps1=0.3#Flow coefficient \n",
+      "N=18000#Speed of the turbine in rpm\n",
+      "Dt=0.42#Rotor tip diameter in m\n",
+      "D2m=0.21#Mean diameter at rotor exit 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",
+      "U1=(3.1415*Dt*N)/60#Peripheral velocity of impeller at inlet in m/s\n",
+      "Cr1=ps1*U1#The radial velocity at inlet in m/s\n",
+      "a11=degrees(atan(Cr1/U1))#The nozzle exit air angle in degree\n",
+      "W=m*U1**2*10**-3#Power developed by turbine in kW\n",
+      "dT=(1/P0)**((r-1)/r)#The total isentropic temperature ratio in entire process \n",
+      "T3s=dT*T00#The final isentropic temperature at exit in K\n",
+      "dh2=W/m#The absolute enthalpy change in the first two stages in kJ/kg\n",
+      "ns=dh2/(Cp*(T00-T3s))#The stage efficiency of the turbine\n",
+      "T02=T00-(W/(m*Cp))#The absolute temperature at the entry of second stage in K\n",
+      "T03=T02#The absolute temperature at exit of second stage in K\n",
+      "dH=Cp*(T02-T3s)#The total enthalpy loss in kJ/kg\n",
+      "dHn=dH/2#The enthalpy loss in the nozzle in kJ/kg\n",
+      "C1=Cr1/sin(pi/180*a11)#Absolute velocity at the inlet in m/s\n",
+      "dH0=((C1**2)/(2000*Cp))+(dHn)#The isentropic absolute enthalpy loss in nozzle in kJ/kg\n",
+      "dT0=dH0/Cp#The isentropic absolute temperature loss in nozzle in K\n",
+      "T1s=T00-dT0#The isentropic temperature at the entry in K\n",
+      "P1=P0*(T1s/T00)**(r/(r-1))#The pressure at the entry of turbine in bar\n",
+      "T1=T00-((C1**2)/(2000*Cp))#The temperature at the entry of turbine in K\n",
+      "d1=(P1*10**5)/(R*T1)#The density of the air at inlet in kg/m**3\n",
+      "b1=m/(d1*Cr1*3.141*Dt)#The width of the rotor at inlet in m\n",
+      "C2=Cr1#The avsolute velocity at the second stage entry in m/s\n",
+      "T2=T02-((C2**2)/(2000*Cp))#The temperature at the second stage entry in K\n",
+      "P23=(T2/T03)**(r/(r-1))#The pressure ratio at the second stage\n",
+      "P2=P23*P3#The pressure at the second stage in bar\n",
+      "d2=(P2*10**5)/(R*T2)#The density of the air at second stage in kg/m**3\n",
+      "C2=Cr1#The absolute velocity at the second stage in m/s\n",
+      "A2=m/(d2*C2)#The area of cross section at the second stage in m**2\n",
+      "h2=(A2/(3.14*D2m))#The rotor blade height at the exit in m\n",
+      "M1=C1/(r*R*T1)**(1/2)#The mach number at the nozzle\n",
+      "U2=(3.14*D2m*N)/60#The Peripheral velocity of impeller at exit in m/s\n",
+      "M2r=(((C2**2)+(U2**2))**(1/2))/(r*R*T2)**(1/2)#The mach number at the rotor exit \n",
+      "Ln=(dHn*10**3)/((C1**2)/2)#The nozzle loss coefficient\n",
+      "Lr=(dHn*10**3)/(((((C2**2)+(U2**2))**(1/2))**2)/2)#The rotor loss coefficient\n",
+      "\n",
+      "#output\n",
+      "print '(a)The nozzle exit air angle is %3.2f degree\\n(b)The power developed is %3.1f kW\\n(c)The stage efficiency is %0.2f %%\\n(d)The rotor width at the entry is %0.2f cm\\n(e)The rotor blade height at the exit is %0.2f cm\\n(f)\\n    (1)The mach number at the nozzle exit is %3.4f\\n    (2)The mach number at the rotor exit is %3.2f\\n(g)\\n    (1)The nozzle loss coefficient is %3.4f\\n    (2)The rotor loss coefficient is %3.3f'%(a11,W,ns*100,b1*100,h2*100,M1,M2r,Ln,Lr)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The nozzle exit air angle is 16.70 degree\n",
+        "(b)The power developed is 1018.4 kW\n",
+        "(c)The stage efficiency is 85.58 %\n",
+        "(d)The rotor width at the entry is 2.76 cm\n",
+        "(e)The rotor blade height at the exit is 9.99 cm\n",
+        "(f)\n",
+        "    (1)The mach number at the nozzle exit is 0.9489\n",
+        "    (2)The mach number at the rotor exit is 0.58\n",
+        "(g)\n",
+        "    (1)The nozzle loss coefficient is 0.1546\n",
+        "    (2)The rotor loss coefficient is 0.496\n"
+       ]
+      }
+     ],
+     "prompt_number": 2
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 6.3 Page 274"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import acos\n",
+      "#input data\n",
+      "ntt=0.9#Total-to-total efficiency\n",
+      "P00=300#The pressure at entry to the nozzle in kPa\n",
+      "T00=1150#The temperature at entry to the nozzle in K\n",
+      "T1=1013#The static temperature at the outlet of the nozzle in K\n",
+      "P03=100#The pressure at the outlet of the diffuser in kPa\n",
+      "R=284.5#The universal gas constant in J/kg.K\n",
+      "Cp=1.147#The specific heat of air at constant pressure in kJ/kg.K\n",
+      "r=1.33#The ratio of specific heats of given gas\n",
+      "\n",
+      "#calculations\n",
+      "U1=(ntt*Cp*1000*T00*(1-((P03/P00)**((r-1)/r))))**(1/2)#The impeller tip speed in m/s\n",
+      "T01=T00#The absolute temperature at the entry in K\n",
+      "C1=(2000*Cp*(T01-T1))**(1/2)#The absolute velocity at the inletof turbine in m/s\n",
+      "a11=acos(pi/180*U1/C1)#The flow angle at the nozzle oulet in degree\n",
+      "M1=C1/(r*R*T1)**(1/2)#The mach number at the nozzle outlet \n",
+      "\n",
+      "#output\n",
+      "print '(a)The impeller tip speed is %3.1f m/s\\n(b)The flow angle at the nozzle oulet is %3.2f degrees\\n(c)The mach number at the nozzle outlet is %3.2f'%(U1,a11,M1)\n",
+      "# answer in the textbook is not correct fot part(b)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The impeller tip speed is 532.2 m/s\n",
+        "(b)The flow angle at the nozzle oulet is 1.55 degrees\n",
+        "(c)The mach number at the nozzle outlet is 0.91\n"
+       ]
+      }
+     ],
+     "prompt_number": 3
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 6.4 Page 275"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "D1=0.09#Rotor inlet tip diameter in m\n",
+      "D2t=0.062#Rotor outlet tip diameter in m\n",
+      "D2h=0.025#Rotor outlet hub diameter in m\n",
+      "N=30000#Blade speed in rpm\n",
+      "d2=1.8#Density of exhaust gases at impeller exit in kg/m**3\n",
+      "C2s=0.447#Ratio of absolute velocity and isentropic velocity at exit\n",
+      "U1Cs=0.707#Ratio of impeller tip velocity and isentropic velocity\n",
+      "\n",
+      "#calculations\n",
+      "U1=(3.1415*D1*N)/60#The impeller tip speed in m/s\n",
+      "Cs=U1/U1Cs#Isentropic velocity in m/s\n",
+      "C2=C2s*Cs#Absolute velocity at the exit in m/s\n",
+      "A2=(3.141/4)*((D2t**2)-(D2h**2))#Area at the exit in m**2\n",
+      "Q2=A2*C2#Volume flow rate at the impeller exit in m**3/s\n",
+      "M=d2*Q2#Mass flow rate in kg/s\n",
+      "W=M*U1**2#Power developed in W\n",
+      "\n",
+      "#output\n",
+      "print '(a)Volume flow rate at the impeller exit is %3.3f m**3/s\\n(b)Power developed is %0.3f kW'%(Q2,W/1000)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Volume flow rate at the impeller exit is 0.226 m**3/s\n",
+        "(b)Power developed is 8.127 kW\n"
+       ]
+      }
+     ],
+     "prompt_number": 4
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 6.5 Page 276"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "P00=3.5#Total-to-static pressure ratio\n",
+      "P2=1#Exit pressure in bar\n",
+      "T00=923#Inlet total temperature in K\n",
+      "U1Cs=0.66#Blade to isentropic speed ratio\n",
+      "D=0.45#Rotor diameter ratio\n",
+      "N=16000#Speed from nozzle in rpm\n",
+      "a11=20#Nozzle exit angle in degree\n",
+      "nn=0.95#Nozzle efficiency\n",
+      "b1=0.05#Rotor width at inlet in m\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",
+      "\n",
+      "#Calculations\n",
+      "T2s=T00*(1/P00)**((r-1)/r)#Isentropic temperature at the exit in K\n",
+      "Cs=(2*Cp*(T00-T2s))**(1/2)#The isentropic velocity in m/s\n",
+      "U1=U1Cs*Cs#The impeller tip speed in m/s\n",
+      "D1=(U1*60)/(3.14*N)#Rotor inlet diameter in m\n",
+      "D2=D*D1#Rotor outlet diameter in m\n",
+      "Cr2=U1*tan(pi/180*a11)#The relative velocity at the exit in m/s\n",
+      "U2=(3.1415*D2*N)/60#Peripheral velocity of impeller at exit in m/s\n",
+      "b22=degrees(atan(Cr2/U2))#The air angle at rotor exit in degree\n",
+      "T02=T00-((U1**2)/(Cp))#The absolute temperature at the exit in K\n",
+      "T2=T02-((Cr2**2)/(2*Cp))#The temperature at the exit of turbine in K\n",
+      "T1=T2+((U1**2)/(2*Cp))#The temperature at the entry of turbine in K\n",
+      "T1s=T00-((T00-T1)/nn)#Isentropic temperature at the entry in K\n",
+      "P1=P00*(T1s/T00)**(r/(r-1))#The pressure at the entry stage in bar\n",
+      "d1=(P1*10**5)/(R*T1)#The density of the air  at the inlet in kg/m**3\n",
+      "A1=3.1415*D1*b1#The area at the inlet in m**2\n",
+      "Cr1=Cr2#The relative velocity at the entry in m/s\n",
+      "m=d1*A1*Cr1#The mass flow rate for a 90degree IFR turbine Degree of Reaction is 0.5 in kg/s\n",
+      "W=(m*U1**2)*10**-6#Power developed in MW\n",
+      "d2=(P2*10**5)/(R*T2)#The density of the air at the exit in kg/m**3\n",
+      "b2=m/(d2*3.141*D2*Cr2)#Rotor width at the exit in m\n",
+      "D2h=D2-b2#Hub diameter at the exit in m\n",
+      "D2t=D2+b2#Tip diameter at the exit in m\n",
+      "nts=(W*10**6)/(m*Cp*(T00-T2s))#Total-to-static efficiency\n",
+      "C1=U1/cos(pi/180*a11)#Absolute velocity at the entry in m/s\n",
+      "Ln=(Cp*(T1-T1s))/((C1**2)/2)#Nozzle enthalpy loss coefficient\n",
+      "W2=((U2**2)+(Cr2**2))**(1/2)#Resultant relative velocity at the exit in m/s\n",
+      "T2s=T1*(P2/P1)**((r-1)/r)#Isentropic temperature at the exit in K\n",
+      "Lr=(Cp*(T2-T2s))/((W2**2)/2)#Rotor enthalpy loss coefficient\n",
+      "\n",
+      "#output\n",
+      "print '(a)\\n    (1)Rotor inlet diameter is %3.2f m\\n    (2)Rotor outlet diameter is %3.3f m\\n(b)The air angle at rotor exit is %3.2f degree\\n(c)The mass flow rate for a 90degree IFR turbine Degree of Reaction is 0.5 is %3.2f kg/s\\n(d)Power developed is %3.3f MW\\n(e)\\n    (1)Hub diameter at the exit is %3.4f m\\n    (2)Tip diameter at the exit is %3.4f m\\n(f)Total-to-static efficiency is %3.4f\\n(g)Nozzle enthalpy loss coefficient is %3.4f\\n(h)Rotor enthalpy loss coefficient is %3.4f'%(D1,D2,b22,m,W,D2h,D2t,nts,Ln,Lr)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)\n",
+        "    (1)Rotor inlet diameter is 0.59 m\n",
+        "    (2)Rotor outlet diameter is 0.265 m\n",
+        "(b)The air angle at rotor exit is 38.95 degree\n",
+        "(c)The mass flow rate for a 90degree IFR turbine Degree of Reaction is 0.5 is 14.21 kg/s\n",
+        "(d)Power developed is 3.456 MW\n",
+        "(e)\n",
+        "    (1)Hub diameter at the exit is 0.0834 m\n",
+        "    (2)Tip diameter at the exit is 0.4466 m\n",
+        "(f)Total-to-static efficiency is 0.8712\n",
+        "(g)Nozzle enthalpy loss coefficient is 0.0526\n",
+        "(h)Rotor enthalpy loss coefficient is 0.3396\n"
+       ]
+      }
+     ],
+     "prompt_number": 5
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 6.6 Page 280"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "P00=700#Total-to-static pressure ratio\n",
+      "T00=1145#Inlet total temperature in K\n",
+      "P1=527#The pressure at the entry stage in bar\n",
+      "T1=1029#The temperature at the entry of turbine in K\n",
+      "P2=385#The pressure at the second stage in bar\n",
+      "T2=915#The temperature at the second stage entry in K\n",
+      "T02=925#The absolute temperature at the exit in K\n",
+      "D2mD1=0.49#The ratio of rotor exit mean diameter to rotor inlet diameter\n",
+      "N=24000#Blade speed in rpm\n",
+      "R1=8.314#The gas constant of given gas in kJ/kg.K\n",
+      "r=1.67#The ratio of specific heats of the gas\n",
+      "m=39.94#Molecular weight of a gas \n",
+      "\n",
+      "#calculations\n",
+      "R=R1/m#The universal gas constant in kJ/kg.K\n",
+      "Cp=(r*R)/(r-1)#The specific heat of air at constant pressure in kJ/kg.K\n",
+      "T2ss=T00*(P2/P00)**((r-1)/r)#Isentropic stage temperature at the exit in K\n",
+      "nts=(T00-T02)/(T00-T2ss)#Total-to-static efficiency of the turbine\n",
+      "U1=(Cp*1000*(T00-T02))**(1/2)#The impeller tip speed in m/s\n",
+      "D1=(U1*60)/(3.1415*N)#Rotor inlet diameter in m\n",
+      "D2m=D1*D2mD1#Rotor exit mean diameter in m\n",
+      "C1=(2*Cp*(T00-T1))**(1/2)#Absolute velocity at the entry in m/s\n",
+      "T1s=T00*(P1/P00)**((r-1)/r)#Isentropic temperature at the entry in K\n",
+      "Ln=(Cp*(T1-T1s))/((C1**2)/2)#Nozzle enthalpy loss coefficient\n",
+      "C2=(2*Cp*1000*(T02-T2))**(1/2)#The temperature at the exit of turbine in K\n",
+      "U2=(3.14*D2m*N)/(60)#Peripheral velocity of impeller at exit in m/s\n",
+      "W2=((C2**2)+(U2**2))**(1/2)#Resultant relative velocity at the exit in m/s\n",
+      "T2s=T1*(P2/P1)**((r-1)/r)#stage temperature at the exit in K\n",
+      "Lr=(Cp*1000*(T2-T2s))/((W2**2)/2)#Rotor enthalpy loss coefficient\n",
+      "ntt=1/((1/nts)-((C2**2)/(2*U1**2)))#Total-to-total efficiency\n",
+      "\n",
+      "#output\n",
+      "print '(a)Total-to-static efficiency of the turbine is %0.1f %%\\n(b)\\n    (1)Rotor inlet diameter is %3.3f m\\n    (2)Rotor exit mean diameter is %3.3f m\\n(c)\\n    (1)Nozzle enthalpy loss coefficient is %3.4f\\n    (2)Rotor enthalpy loss coefficient is %3.4f\\n(d)Total-to-total efficiency is %0.2f %%'%(nts*100,D1,D2m,Ln,Lr,ntt*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Total-to-static efficiency of the turbine is 90.1 %\n",
+        "(b)\n",
+        "    (1)Rotor inlet diameter is 0.269 m\n",
+        "    (2)Rotor exit mean diameter is 0.132 m\n",
+        "(c)\n",
+        "    (1)Nozzle enthalpy loss coefficient is 0.0625\n",
+        "    (2)Rotor enthalpy loss coefficient is 0.2138\n",
+        "(d)Total-to-total efficiency is 93.95 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 6
+    }
+   ],
+   "metadata": {}
+  }
+ ]
+}
\ No newline at end of file
diff --git a/Turbomachines_by_A._V._Arasu/Ch7.ipynb b/Turbomachines_by_A._V._Arasu/Ch7.ipynb
new file mode 100644
index 00000000..901a931e
--- /dev/null
+++ b/Turbomachines_by_A._V._Arasu/Ch7.ipynb
@@ -0,0 +1,429 @@
+{
+ "metadata": {
+  "name": "",
+  "signature": "sha256:f827c11afa624e3e81bfed710ad978d27a2bfba89c05ec909ef7162ba7b3cadb"
+ },
+ "nbformat": 3,
+ "nbformat_minor": 0,
+ "worksheets": [
+  {
+   "cells": [
+    {
+     "cell_type": "heading",
+     "level": 1,
+     "metadata": {},
+     "source": [
+      "Chapter 7 - Dimensional and Modal Analysis"
+     ]
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 7.5 Page 312"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from __future__ import division\n",
+      "#input data\n",
+      "Nm=1000#Speed of the model in rpm\n",
+      "Hm=8#Head of the model in m\n",
+      "Pm=30#Power of the model in kW\n",
+      "Hp=25#Head of the prototype in m\n",
+      "DmDp=1/5#The scale of the model to original\n",
+      "\n",
+      "#calculations\n",
+      "Np=((Hp/Hm)**(1/2))*(DmDp)*(Nm)#Speed of the prototype in rpm\n",
+      "Pp=(Pm)*((1/DmDp)**(5))*(Np/Nm)**(3)#Power developed by the prototype in kW\n",
+      "QpQm=((1/DmDp)**(3))*(Np/Nm)#Ratio of the flow rates of two pump(model and prototype)\n",
+      "\n",
+      "#output\n",
+      "print '(1)Speed of prototype pump is %3.1f rpm\\n(2)Power developed by the prototype pump is %3i kW\\n(3)Ratio of the flow rates of two pumps is %3.4f'%(Np,Pp,QpQm)\n"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(1)Speed of prototype pump is 353.6 rpm\n",
+        "(2)Power developed by the prototype pump is 4143 kW\n",
+        "(3)Ratio of the flow rates of two pumps is 44.1942\n"
+       ]
+      }
+     ],
+     "prompt_number": 1
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 7.6 Page 313"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "Hp=85#Head of the prototype in m\n",
+      "Qp=(20000/3600)#Flow rate of the prototype in m**3/s\n",
+      "Np=1490#Speed of the prototype in rpm\n",
+      "Dp=1.2#Diameter of the prototype in m\n",
+      "dp=714#Density of the prototype fluid in kg/m**3\n",
+      "Pp=4#Power of the prototype in MW\n",
+      "Pm=500*10**-3#Power of the model in MW\n",
+      "Qm=0.5#Flow rate of the prototype in m**3/s\n",
+      "dm=1000#Density of the model fluid (water) in kg/m**3\n",
+      "\n",
+      "#calculations\n",
+      "NpNm=(Qp/Qm)#Ratio of the speeds of the prototype and the model in terms of (Dm/Dp)**(3)\n",
+      "DmDp=1/(((NpNm)**(3))*(dp/dm)*(Pm/Pp))**(1/4)#The ratio of the diameters of model and the prototype or the scale ratio \n",
+      "NmNp=1/(NpNm*((DmDp)**(3)))#The speed ratio or the ratio of speeds of the model and the prototype\n",
+      "HmHp=((1/NmNp)**(2))*((1/DmDp)**(2))#The head ratio or the ratio of heads of the model and the prototype \n",
+      "\n",
+      "#output\n",
+      "print '(1)The head ratio of the model is %3.1f\\n(2)The speed ratio of the model is %3.1f\\n(3)The scale ratio of the model is %3.1f'%(HmHp,NmNp,DmDp)\n",
+      "# Answer in the textbook is wrong"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(1)The head ratio of the model is 1.0\n",
+        "(2)The speed ratio of the model is 3.3\n",
+        "(3)The scale ratio of the model is 0.3\n"
+       ]
+      }
+     ],
+     "prompt_number": 2
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 7.7 Page 315"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "Np=400#The speed of the prototype in rpm\n",
+      "Qp=1.7#The discharge of the prototype in m**3/s\n",
+      "Hp=36.5#The head of the prototype in m\n",
+      "Pp=720#The power input of the prototype in kW\n",
+      "Hm=9#The head of the model in m\n",
+      "DmDp=1/6#The scale of model to prototype \n",
+      "\n",
+      "#calculations\n",
+      "Nm=((Hm/Hp)**(1/2))*(1/DmDp)*Np#Speed of the model in rpm\n",
+      "Qm=((DmDp)**(3))*(Nm/Np)*(Qp)#Discharge of the model in m**3/s\n",
+      "Pm=((DmDp)**(5))*((Nm/Np)**(3))*Pp#Power required by the model in kW\n",
+      "\n",
+      "#output\n",
+      "print '(a)Speed of the model is %3.2f rpm\\n(b)Discharge of the model is %3.4f m**3/s\\n(c)Power required by the model is %3.2f kW'%(Nm,Qm,Pm)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Speed of the model is 1191.75 rpm\n",
+        "(b)Discharge of the model is 0.0234 m**3/s\n",
+        "(c)Power required by the model is 2.45 kW\n"
+       ]
+      }
+     ],
+     "prompt_number": 3
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 7.8 Page 316"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "N1=1000#The running speed of the pump-1 in rpm\n",
+      "D1=0.3#The impeller diameter of pump-1 in m\n",
+      "Q1=0.02#The discharge of pump-1 in m**3/s\n",
+      "H1=15#The head developed by the pump-1 in m\n",
+      "N2=1000#The running speed of the pump-2 in rpm\n",
+      "Q2=0.01#The discharge of pump-2 in m**3/s\n",
+      "\n",
+      "#calculations\n",
+      "D2=(((Q2/Q1)*(N1/N2))**(1/3))*(D1)#Impeller diameter of the pump-2 in m\n",
+      "H2=(((D2/D1)*(N2/N1))**(2))*(H1)#Head developed by the pump-2 in m\n",
+      "\n",
+      "#output\n",
+      "print '(a)Impeller diameter of the pump-2 is %3.3f m\\n(b)Head developed by the pump-2 is %3.2f m'%(D2,H2)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Impeller diameter of the pump-2 is 0.238 m\n",
+        "(b)Head developed by the pump-2 is 9.45 m\n"
+       ]
+      }
+     ],
+     "prompt_number": 4
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 7.9 Page 316"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "DmDp=1/10#The model ratio to prototype \n",
+      "Pm=1.84#Power developed by the model in kW\n",
+      "Hm=5#Head developed by the model in m\n",
+      "Nm=480#Speed of the model in rpm\n",
+      "Hp=40#Head developed by the prototype in m\n",
+      "\n",
+      "#calculations\n",
+      "Np=((Hp/Hm)**(1/2))*(DmDp)*(Nm)#Speed of the prototype in rpm\n",
+      "Pp=((1/DmDp)**(5))*((Np/Nm)**(3))*Pm#Power developed by the prototype in kW\n",
+      "Nsp=((Np*((Pp)**(1/2)))/((Hp)**(5/4)))#Specific speed of the prototype\n",
+      "Nsm=((Nm*((Pm)**(1/2)))/((Hm)**(5/4)))#Specific speed of the prototype\n",
+      "\n",
+      "#output\n",
+      "print '(a)Power developed by the prototype is %3i kW\\n(b)Speed of the prototype is %3.2f rpm\\n(c)Specific speed of the prototype is %3.1f\\n(d)Specific speed of the model is %3.1f\\n Thus the specific speed of the model is equal to the prototype and thus it is verified'%(Pp,Np,Nsp,Nsm)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Power developed by the prototype is 4163 kW\n",
+        "(b)Speed of the prototype is 135.76 rpm\n",
+        "(c)Specific speed of the prototype is 87.1\n",
+        "(d)Specific speed of the model is 87.1\n",
+        " Thus the specific speed of the model is equal to the prototype and thus it is verified\n"
+       ]
+      }
+     ],
+     "prompt_number": 5
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 7.10 Page 317"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from __future__ import division\n",
+      "#input data\n",
+      "DmDp=1/10#The model ratio to prototype\n",
+      "Hm=5#The head developed by the model in m\n",
+      "Hp=8.5#The head developed by the prototype in m\n",
+      "Pp=8000*10**3#The power developed by the prototype in W\n",
+      "Np=120#The speed of running of the prototype in rpm\n",
+      "d=1000#density of the water in kg/m**3\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "n0=0.85#Overall efficiency of the prototype\n",
+      "\n",
+      "#calculations\n",
+      "Nm=((Hm/Hp)**(1/2))*(1/DmDp)*(Np)#Speed of the mpdel in rpm\n",
+      "Qp=Pp/(d*g*n0*Hp)#Discharge from the prototype in m**3/s\n",
+      "Qm=((DmDp)**(3))*(Nm/Np)*(Qp)#Discharge from the model in m**3/s\n",
+      "Pm=((DmDp)**(5))*((Nm/Np)**(3))*(Pp)*10**-3#Power of the model in kW\n",
+      "\n",
+      "#output\n",
+      "print '(a)Speed of the model is %3.1f rpm\\n(b)Discharge from the model is %3.3f m**3/s\\n(c)Power of the model is %3.1f kW'%(Nm,Qm,Pm)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Speed of the model is 920.4 rpm\n",
+        "(b)Discharge from the model is 0.866 m**3/s\n",
+        "(c)Power of the model is 36.1 kW\n"
+       ]
+      }
+     ],
+     "prompt_number": 6
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 7.11 Page 318"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "P1=6600#Initial power developed by the turbine in kW\n",
+      "N1=100#Initial speed of the turbine in rpm\n",
+      "H1=30#Initial head of the turbine in m\n",
+      "H2=18#Final head of the turbine in m\n",
+      "\n",
+      "#calculations\n",
+      "N2=N1*((H2/H1)**(1/2))#The final speed of the turbine in rpm\n",
+      "P2=P1*((H2/H1)**(3/2))#The final power developed by the turbine in kW\n",
+      "\n",
+      "#output\n",
+      "print '(1)The final speed of the turbine is %3.2f rpm\\n(2)The final power developed by the turbine is %3i kW'%(N2,P2)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(1)The final speed of the turbine is 77.46 rpm\n",
+        "(2)The final power developed by the turbine is 3067 kW\n"
+       ]
+      }
+     ],
+     "prompt_number": 7
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 7.12 Page 319"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "H1=25#The initial head on the turbine in m\n",
+      "N1=200#The initial speed of the turbine in rpm \n",
+      "Q1=9#The initial discharge of the turbine in m**3/s\n",
+      "n0=0.9#Overall efficiency of the turbine \n",
+      "H2=20#The final head on the turbine in m\n",
+      "d=1000#density of the water in kg/m**3\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "\n",
+      "#calculations\n",
+      "N2=N1*((H2/H1)**(1/2))#The final speed of the turbine in rpm\n",
+      "Q2=Q1*((H2/H1)**(1/2))#The final discharge of the  turbine in m**3/s\n",
+      "P1=n0*d*g*Q1*H1*10**-3#Power produced by the turbine initially in kW\n",
+      "P2=P1*((H2/H1)**(3/2))#Power produced by the turbine finally in kW\n",
+      "\n",
+      "#output\n",
+      "print '(a)The final speed of the turbine is %3.2f rpm\\n(b)The final discharge of the  turbine is %3.2f m**3/s\\n(c)Power produced by the turbine initially is %3.3f kW\\n(d)Power produced by the turbine finally is %3.2f kW'%(N2,Q2,P1,P2)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The final speed of the turbine is 178.89 rpm\n",
+        "(b)The final discharge of the  turbine is 8.05 m**3/s\n",
+        "(c)Power produced by the turbine initially is 1986.525 kW\n",
+        "(d)Power produced by the turbine finally is 1421.44 kW\n"
+       ]
+      }
+     ],
+     "prompt_number": 8
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 7.13 Page 320"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "P1=5000*10**3#The initial power produced in W\n",
+      "H1=250#The initial head produced in m\n",
+      "N1=210#The initial speed of turbine in rpm\n",
+      "n0=0.85#Overall efficiency of the turbine \n",
+      "H2=160#The final head produced in m\n",
+      "d=1000#density of the water in kg/m**3\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "\n",
+      "\n",
+      "#calculations\n",
+      "Nu=N1/((H1)**(1/2))#The unit speed of the turbine \n",
+      "Pu=P1/((H1)**(3/2))*10**-3#The unit power of the turbine \n",
+      "Q1=P1/(d*g*n0*H1)#The initial discharge of the turbine in m**3/s\n",
+      "Qu=Q1/((H1)**(1/2))#The unit discharge of the turbine \n",
+      "Q2=Qu*((H2)**(1/2))#The final discharge of the turbine in  m**3/s\n",
+      "N2=Nu*((H2)**(1/2))#The final speed of the turbine in rpm\n",
+      "P2=Pu*((H2)**(3/2))#The final power of the turbine in kW\n",
+      "Ns=(N2*((P2)**(1/2)))/((H2)**(5/4))#The specific speed of the turbine\n",
+      "\n",
+      "#output\n",
+      "print '(a)The unit speed of the turbine is %3.2f\\n(b)The unit power of the turbine is %3.3f\\n(c)The unit discharge of the turbine is %3.3f\\n(d)The final discharge of the turbine is %3.2f m**3/s\\n(e)The final speed of the turbine is %3.2f rpm\\n(f)The final power of the turbine is %3.1f kW\\n(g)The specific speed of the turbine is %3.2f'%(Nu,Pu,Qu,Q2,N2,P2,Ns)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The unit speed of the turbine is 13.28\n",
+        "(b)The unit power of the turbine is 1.265\n",
+        "(c)The unit discharge of the turbine is 0.152\n",
+        "(d)The final discharge of the turbine is 1.92 m**3/s\n",
+        "(e)The final speed of the turbine is 168.00 rpm\n",
+        "(f)The final power of the turbine is 2560.0 kW\n",
+        "(g)The specific speed of the turbine is 14.94\n"
+       ]
+      }
+     ],
+     "prompt_number": 9
+    }
+   ],
+   "metadata": {}
+  }
+ ]
+}
\ No newline at end of file
diff --git a/Turbomachines_by_A._V._Arasu/Ch8.ipynb b/Turbomachines_by_A._V._Arasu/Ch8.ipynb
new file mode 100644
index 00000000..76640a4f
--- /dev/null
+++ b/Turbomachines_by_A._V._Arasu/Ch8.ipynb
@@ -0,0 +1,1122 @@
+{
+ "metadata": {
+  "name": "",
+  "signature": "sha256:4917afa3531ad5b8b88974bc3a67730d6fe85dd6094df74e9d2ebeeb54dc0430"
+ },
+ "nbformat": 3,
+ "nbformat_minor": 0,
+ "worksheets": [
+  {
+   "cells": [
+    {
+     "cell_type": "heading",
+     "level": 1,
+     "metadata": {},
+     "source": [
+      "Chapter8 - Hydraulic pumps"
+     ]
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 8.1 Page 354"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from __future__ import division\n",
+      "from math import pi, tan\n",
+      "#input data\n",
+      "D=1.3#Diameter of the pump in m\n",
+      "Q=3.5/60#Discharge of water by pump in m**3/s\n",
+      "U2=10#Tip speed of pump in m/s\n",
+      "Cr2=1.6#Flow velocity of water in pump in m/s\n",
+      "b2=30#Outlet blade angle tangent to impeller periphery in degree\n",
+      "Cx1=0#Whirl velocity at inlet in m/s\n",
+      "U=10#Tip speed of pump in m/s\n",
+      "d=1000#Density of water in kg/m**3\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "\n",
+      "#calculations\n",
+      "Wx2=Cr2/tan(b2*pi/180)#Exit relative velocity in m/s\n",
+      "E=(U2/g)*(U2-(Wx2))#Euler head in m or W/(N/S)\n",
+      "m=d*Q#Mass flow rate of water in kg/s\n",
+      "W=E*m*g#Power delivered in W\n",
+      "r=D/2#Radius of the pump in m\n",
+      "T=W/(U/r)#Torque delivered in Nm\n",
+      "\n",
+      "#output\n",
+      "print 'Torque delivered by the impeller is %3.1f Nm'%(T)\n",
+      "# Answer in the textbook is wrong."
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "Torque delivered by the impeller is 274.1 Nm\n"
+       ]
+      }
+     ],
+     "prompt_number": 1
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 8.2 Page 355"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import sin, tan\n",
+      "#input data\n",
+      "b2=30#Impeller blade angle to the tangent at impeller outlet in degree\n",
+      "d=0.02#Blade depth in m\n",
+      "D=0.25#Blade diameter in m\n",
+      "N=1450#Pump rotation speed in rpm\n",
+      "Q=0.028#FLow rate of the pump in m**3/s\n",
+      "sf=0.77#Slip factor \n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "\n",
+      "#calculations\n",
+      "A=3.1415*d*D#Flow area in m**2\n",
+      "Cr2=Q/A#Flow velocity in m/s\n",
+      "Wx2=Cr2/tan(b2*pi/180)#Exit relative velocity in m/s\n",
+      "U2=(3.14*D*N)/60#Tip speed of pump in m/s\n",
+      "Cx2=U2-Wx2#Absolute whirl component at exit in m/s\n",
+      "E=(U2*Cx2)/g#Euler head with no whirl at inlet in m\n",
+      "Cx21=sf*Cx2#Actual value of component of absolute value in tangential direction in m/s\n",
+      "Es=sf*E#Theoretical head with slip in m\n",
+      "Z=(3.145*sin(b2*pi/180))/((1-sf)*(1-((Cr2/U2)/tan(b2*pi/180))))#Number of blades required based on stodola slip factor\n",
+      "\n",
+      "#output\n",
+      "print '(a)Theoretical head with slip is %3.2f m\\n(b)Number of blades required is %3.f'%(Es,Z)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Theoretical head with slip is 23.65 m\n",
+        "(b)Number of blades required is   8\n"
+       ]
+      }
+     ],
+     "prompt_number": 2
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 8.3 Page 356"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "D2=0.4#Outer diameter of impeller in m\n",
+      "b2=0.05#Outlet width of impeller in m\n",
+      "N=800#Running speed of pump in rpm\n",
+      "Hm=16#Working head of pump in m\n",
+      "b22=40#Vane angle at outlet in degree\n",
+      "nm=0.75#Manometric efficiency \n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "\n",
+      "#calculations\n",
+      "U2=(3.1415*D2*N)/60#Impeller tip speed in m/s\n",
+      "Cx2=(g*Hm)/(U2*nm)#Absolute whirl component at exit in m/s\n",
+      "Wx2=U2-Cx2#Exit relative velocity in m/s\n",
+      "Cr2=Wx2*tan(b22*pi/180)#Flow velocity of water in pump in m/s\n",
+      "A=3.14*D2*b2#Area of flow in m**2\n",
+      "Q=A*Cr2#Discharge of the pump in m**3/s\n",
+      "\n",
+      "#output\n",
+      "print 'The discharge of the pump is %3.4f m**3/s'%(Q)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "The discharge of the pump is 0.2247 m**3/s\n"
+       ]
+      }
+     ],
+     "prompt_number": 3
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 8.4 Page 357"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import tan, atan, degrees\n",
+      "#input data\n",
+      "D2D1=2#The ratio of outer and inner diameter \n",
+      "N=1200#The running speed of pump in rpm\n",
+      "Hm=75#Total head producing work in m\n",
+      "Cr1=3#Flow velocity through impeller at inlet in m/s\n",
+      "Cr2=Cr1#Flow velocity through impeller at outlet in m/s\n",
+      "b22=30#Vanes set back angle at outlet in degree\n",
+      "D2=0.6#Outlet diameter of impeller in m\n",
+      "d=1000#Density of water in kg/m**3\n",
+      "b2=0.05#Width of impeller at outlet in m\n",
+      "g=9.81#Acceleartion due to gravity in m/s**2\n",
+      "\n",
+      "#calculations\n",
+      "D1=D2/D2D1#Inlet diameter of impeller in m\n",
+      "U1=(3.1415*D1*N)/60#Impeller tip speed at inlet in m/s\n",
+      "b11=degrees(atan(Cr1/U1))#Vane angle at inlet in degree\n",
+      "U2=(3.1415*D2*N)/60#Impeller tip speed at exit in m/s\n",
+      "A=3.1415*D2*b2#Area of flow in m**2\n",
+      "Q=A*Cr2#Discharge of the pump in m**/s\n",
+      "m=d*Q#Mass flow rate of water in kg/s\n",
+      "Wx2=Cr2/tan(b22*pi/180)#Exit relative velocity in m/s\n",
+      "Cx2=U2-Wx2#Absolute whirl component at exit in m/s\n",
+      "W=m*U2*Cx2*10**-3#Work done per second in kW\n",
+      "nm=Hm/((U2*Cx2)/g)#Manometric efficiency \n",
+      "\n",
+      "#output\n",
+      "print '(a)Vane angle at inlet is %3.3f degree\\n(b)Work done per second is %3.2f kW\\n(c)Manometric efficiency is %0.2f %%'%(b11,W,nm*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Vane angle at inlet is 9.043 degree\n",
+        "(b)Work done per second is 346.42 kW\n",
+        "(c)Manometric efficiency is 60.05 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 4
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 8.5 Page 358"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "Q=75#Discharge from the pump in l/s\n",
+      "D1=0.1#Inlet diameter of the pump in m\n",
+      "D2=0.29#Outlet diameter of the pump in m \n",
+      "Hm=30#Total head producing work in m\n",
+      "N=1750#Speed of the pump in rpm\n",
+      "b1=0.025#Width of impeller at inlet per side in m\n",
+      "b2=0.023#Width of impeller at outlet in total in m\n",
+      "a11=90#The angle made by the entering fluid to impeller in degree\n",
+      "b22=27#Vanes set back angle at outlet in degree\n",
+      "Qloss=2.25#Leakage loss in l/s\n",
+      "ml=1.04#Mechanical loss in kW\n",
+      "cf=0.87#Contraction factor due to vane thickness \n",
+      "n0=0.55#Overall efficiency\n",
+      "d=1000#Density of water in kg/m**3\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "\n",
+      "#calculations\n",
+      "U1=(3.1415*D1*N)/60#Blade inlet speed in m/s\n",
+      "A1=3.1415*D1*b1*cf*10**3#Area of flow at inlet in m**2\n",
+      "Qt=Q+Qloss#Total quantity of water handled by pump in l/s\n",
+      "Qts=Qt/2#Total quantity of water handled by pump per side in l/s\n",
+      "Cr1=(Qts*10**-3)/(A1*10**-3)#Flow velocity through impeller at inlet in m/s\n",
+      "b11=degrees(atan(Cr1/U1))#Inlet vane angle in degree\n",
+      "A2=3.1415*D2*(b2/2)*cf*10**3#Area of flow at outlet in m**2 here b2 is calculated per side\n",
+      "Cr2=Qts/A2#Velocity of flow at outlet in m/s\n",
+      "U2=(3.1415*D2*N)/60#Peripheral speed at outlet in m/s\n",
+      "Wx2=Cr2/tan(b22*pi/180)#Exit relative velocity in m/s\n",
+      "Cx2=U2-Wx2#Absolute whirl component at exit in m/s\n",
+      "a22=degrees(atan(Cr2/Cx2))#The absolute water angle at outlet in degree\n",
+      "C2=Cr2/sin(a22*pi/180)#Absolute velocity of water at exit in m/s\n",
+      "nh=Hm/((U2*Cx2)/g)#Manometric efficiency \n",
+      "nv=Q/Qt#Volumetric efficiency \n",
+      "SP=(d*g*(Q*10**-3/2)*Hm)/n0*10**-3#Shaft power in kW\n",
+      "nm=(SP-ml)/SP#Mechanical efficiency \n",
+      "\n",
+      "#output\n",
+      "print '(a)Inlet vane angle is %3.2f degree\\n(b)The absolute water angle is %3.2f degree\\n(c)Absolute velocity of water at exit is %3.2f m/s\\n(d)Manometric efficiency is %0.1f %%\\n(e)Volumetric efficiency is %0.2f %%\\n(f)Mechanical efficiency is %0.1f %%'%(b11,a22,C2,nh*100,nv*100,nm*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Inlet vane angle is 31.67 degree\n",
+        "(b)The absolute water angle is 13.07 degree\n",
+        "(c)Absolute velocity of water at exit is 18.74 m/s\n",
+        "(d)Manometric efficiency is 60.7 %\n",
+        "(e)Volumetric efficiency is 97.09 %\n",
+        "(f)Mechanical efficiency is 94.8 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 5
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 8.6 Page 360"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "Hi=0.25#Vaccum gauge reading in m of Hg vaccum\n",
+      "P0=1.5#Pressure gauge reading in bar\n",
+      "Z01=0.5#Effective height between gauges in m\n",
+      "P=22#Power of electric motor in kW\n",
+      "Di=0.15#Inlet diameter in m\n",
+      "Do=0.15#Outlet diameter in m\n",
+      "Q=0.1#Discharge of pump in m**3/s\n",
+      "dHg=13600#Density of mercury in kg/m**3\n",
+      "dw=1000#Density of water in kg/m**3\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "\n",
+      "#calculations\n",
+      "Pi=dHg*g*Hi#Inlet pressure in N/m**2 vaccum\n",
+      "Po=P0*10**5#Outlet pressure in N/m**2\n",
+      "V0=Q/((3.1415*Do**2)/4)#Velocity of water in delivery pipe in m/s\n",
+      "Vi=V0#vleocity of water in suction pipe in m/s\n",
+      "Hm=((Po+Pi)/(dw*g))+((V0**2-Vi**2)/(2*g))+(Z01)#Manometric head in m\n",
+      "n0=(dw*g*Q*Hm)/(P*10**3)#Overall efficiency \n",
+      "\n",
+      "#output\n",
+      "print '(a)Manometric head is %3.2f m\\n(b)Overall efficiency is %0.1f %%'%(Hm,n0*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Manometric head is 19.19 m\n",
+        "(b)Overall efficiency is 85.6 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 6
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 8.7 Page 361"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "Hm=20#Head against which work is produced in pump in m\n",
+      "b22=45#Vanes set back angle at outlet in degree\n",
+      "N=600#Rotating speed of pump in rpm\n",
+      "Cr1=2#Flow velocity through impeller at inlet in m/s\n",
+      "Cr2=Cr1#Flow velocity through impeller at outlet in m/s\n",
+      "g=9.81#acceleration due to gravity in m/s**2\n",
+      "\n",
+      "#calculations\n",
+      "Wx2=Cr2/tan(b22*pi/180)#Exit relative velocity in m/s\n",
+      "U2=(4+(16+(4*3*792.8))**(1/2))/(2*3)#   Blade outlet speed in m/s\n",
+      "     #The above equation is obtained by solving \n",
+      "     #Cx2=U2-Wx2     #Absolute whirl component at exit in m/s\n",
+      "     #C2=(Cx2**2+Cr2**2)**(1/2)    #Absolute velocity of water at exit in m/s\n",
+      "     #Hm=(U2*Cx2/g)-((C2**2)/(4*g))     #Total head producing work in m\n",
+      "     #3*(U2**2)-(4*U2)-792.8=0       \n",
+      "D2=(60*U2)/(3.1415*N)#Impeller diameter in m\n",
+      "\n",
+      "#output\n",
+      "print 'The impeller diameter is %3.4f m'%(D2)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "The impeller diameter is 0.5391 m\n"
+       ]
+      }
+     ],
+     "prompt_number": 7
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 8.8 Page 362"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "n0=0.7#Overall efficiency\n",
+      "Q=0.025#Discharge of water by the pump in m**3/s\n",
+      "H=20#Height of supplied by the pump in m\n",
+      "D=0.1#Diameter of the pump in m\n",
+      "L=100#Length of the pipe in m\n",
+      "f=0.012#Friction coefficient \n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "d=1000#Density of water in kg/m**3\n",
+      "\n",
+      "#calculations\n",
+      "V0=Q/((3.1415/4)*D**2)#Velocity of water in the pipe in m/s\n",
+      "hf0=(4*f*L*V0**2)/(2*g*D)#Loss of head due to friction in pipe in m\n",
+      "Hm=H+hf0+(V0**2/(2*g))#Manometric head in m\n",
+      "P=(d*g*Q*Hm)/(n0)*10**-3#Power required to drive the pump in kW\n",
+      "\n",
+      "#output\n",
+      "print 'Power required to drive the pump is %3.2f kW'%(P)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "Power required to drive the pump is 15.87 kW\n"
+       ]
+      }
+     ],
+     "prompt_number": 8
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 8.9 Page 363"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "Q=0.015#Discharge of water in pump in m**3/s\n",
+      "D1=0.2#Internal diameter of the impeller in m\n",
+      "D2=0.4#External diameter of the impeller in m\n",
+      "b1=0.016#Width of impeller at inlet in m\n",
+      "b2=0.008#Width of impeller at outlet in m\n",
+      "N=1200#Running speed of the pump in rpm\n",
+      "b22=30#Impeller vane angle at outlet in degree\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "d=1000#Density of water in kg/m**3\n",
+      "\n",
+      "#calculations\n",
+      "print 'From velocity triangles the following values have been deduced'\n",
+      "a11=90#The absolute water angle at inlet in degree\n",
+      "Cx1=0#Absolute whirl component at inlet in m/s\n",
+      "A1=3.1415*D1*b1#Area of flow at inlet in m**2\n",
+      "Cr1=Q/A1#Flow velocity through impeller at inlet in m/s\n",
+      "C1=Cr1#Absolute velocity at inlet in m/s\n",
+      "A2=3.1415*D2*b2#Area of flow at outlet in m**2\n",
+      "Cr2=Q/A2#Flow velocity through impeller at outlet in m/s\n",
+      "U2=(3.1415*D2*N)/60#Blade outlet speed in m/s\n",
+      "Cx2=U2-(Cr2/tan(b22*pi/180))#Absolute whirl component at outlet in m/s\n",
+      "C2=(Cx2**2+Cr2**2)**(1/2)#Velocity at impeller exit in m/s\n",
+      "Ihl=((Cx2*U2)/g)-((C2**2)/(2*g))+((C1**2)/(2*g))#Pressure rise in impeller in m\n",
+      "\n",
+      "#output\n",
+      "print '\\n\\nThe rise in pressure in the impeller is %3.3f m'%(Ihl)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "From velocity triangles the following values have been deduced\n",
+        "\n",
+        "\n",
+        "The rise in pressure in the impeller is 31.852 m\n"
+       ]
+      }
+     ],
+     "prompt_number": 9
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 8.10 Page 365"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "Ihl=3#Head loss in impeller in m\n",
+      "Cr2=4.64#Flow velocity through impeller at outlet in m/s\n",
+      "U2=30#Blade outlet speed in m/s\n",
+      "dPi=35.3#Difference in pressure gauge readings at impeller inlet and outlet in m of water\n",
+      "Pg=4.7#Pressure gain in the casing in m of water \n",
+      "n=0.385#Part of absolute kinetic energy converted into pressure gain\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "d=1000#Density of water in kg/m**3\n",
+      "ss=0.85#Slip coefficient\n",
+      "\n",
+      "#calculations\n",
+      "Kei=Pg/n#Kinetic energy at impeller exit in m/s\n",
+      "C2=((Kei)*2*g)**(1/2)#Velocity at impeller exit in m/s\n",
+      "Cx22=(C2**2-Cr2**2)**(1/2)#Absolute whirl component at outlet with fliud slip in m/s\n",
+      "Cx2=Cx22/ss#Ideal absolute whirl velocity in m/s\n",
+      "b22=degrees(atan(Cr2/(U2-Cx2)))#Blade angle at exit in degree\n",
+      "Wm=ss*U2*Cx2#Euler work input in J/kg\n",
+      "nm=dPi/(U2*Cx22/g)#Manometric efficiency\n",
+      "dP=(U2*Cx22/g)-(Ihl)-(C2**2/(2*g))#Pressure rise in impeller in m\n",
+      "\n",
+      "#output\n",
+      "print '(a)\\n    Exit blade angle is %3.2f degree\\n    Euler work input is %3.2f J/kg\\n(b)Manometric efficiency is %0.2f %%\\n(c)Pressure rise in the impeller is %3.3f m'%(b22,Wm,nm*100,dP)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)\n",
+        "    Exit blade angle is 20.17 degree\n",
+        "    Euler work input is 442.93 J/kg\n",
+        "(b)Manometric efficiency is 78.18 %\n",
+        "(c)Pressure rise in the impeller is 29.943 m\n"
+       ]
+      }
+     ],
+     "prompt_number": 10
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 8.11 Page 366"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "r1=0.051#Eye radius of the impeller in m\n",
+      "D2=0.406#Outer diameter of the impeller in m\n",
+      "b11=(90-75)#Inlet blade angle measured from tangential flow direction in degree\n",
+      "b22=(90-83)#Outlet blade angle measured from tangential flow direction in degree\n",
+      "b=0.064#Blade depth in m\n",
+      "Cx1=0#Inlet whirl velocity in m/s\n",
+      "nh=0.89#Hydraulic efficiency \n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "d=1000#Density of water in kg/m**3\n",
+      "N=900#Rotating speed of impeller in rpm\n",
+      "\n",
+      "#calculations\n",
+      "w=(2*3.1415*N)/60#Angular velocity at inlet in rad/s\n",
+      "U1=(w*r1)#Inlet tangential impeller velocity in m/s\n",
+      "C1=U1*tan(b11*pi/180)#Velocity at impeller inlet in m/s\n",
+      "A=2*3.1415*r1*b#Area of flow through the pump in m**2\n",
+      "Cr1=C1#Flow velocity through impeller at inlet in m/s\n",
+      "Q=A*Cr1#Volume flow through the pump in m**3/s\n",
+      "r2=D2/2#Outer radius of the impeller in m\n",
+      "Cr2=(r1*Cr1)/r2#Flow velocity through impeller at outlet in m/s\n",
+      "U2=w*r2#Outlet tangential impeller velocity in m/s\n",
+      "Wx2=Cr2/tan(b22*pi/180)#Exit relative velocity in m/s\n",
+      "E=(U2/g)*(U2-Wx2)#Theoretical head developed in m\n",
+      "Hm=nh*E#Total stagnation head developed by the pump in m\n",
+      "dP021=Hm*d*g*10**-3#Total pressure head coefficient in kPa\n",
+      "Cx2=U2-(Cr2/tan(b22*pi/180))#Absolute whirl velocity in m/s\n",
+      "C2=(Cr2**2+Cx2**2)**(1/2)#Velocity at impeller exit in m/s\n",
+      "dP21=(Hm-(((C2**2)-(C1**2))/(2*g)))*d*g*10**-3#The static pressure head in kPa\n",
+      "P=d*g*Q*Hm*10**-3#Power given to the fluid in kW\n",
+      "Ps=P/nh#Input power to impeller in kW\n",
+      "\n",
+      "#output\n",
+      "print '(a)Volume flow rate through the impeller is %3.4f m**3/s\\n(b)\\n    stagnation pressure rise across the impeller is %3.1f kPa\\n    Static pressure rise across the impeller is %3.1f kPa\\n(c)Power given to fluid is %3.2f kW\\n(d)Input power to impeller is %3.2f kW'%(Q,dP021,dP21,P,Ps)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Volume flow rate through the impeller is 0.0264 m**3/s\n",
+        "(b)\n",
+        "    stagnation pressure rise across the impeller is 280.9 kPa\n",
+        "    Static pressure rise across the impeller is 145.6 kPa\n",
+        "(c)Power given to fluid is 7.42 kW\n",
+        "(d)Input power to impeller is 8.34 kW\n"
+       ]
+      }
+     ],
+     "prompt_number": 11
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 8.12 Page 368"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import pi, tan\n",
+      "from __future__ import division\n",
+      "#input data\n",
+      "Q=0.04#Discharge of the pump design in m**3/s\n",
+      "Ns=0.075#Specific speed in rev\n",
+      "b22=(180-120)#Outlet angle with the normal in degree\n",
+      "H=35#Distance to which pumping of water is done in m\n",
+      "Dp=0.15#Diameter of suction and delivery pipes in m\n",
+      "L=40#Combined length of suction and delivery pipes in m\n",
+      "WD=1/10#Width to diameter ratio at outlet of impeller \n",
+      "f=0.005#Friction factor \n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "nh=0.76#Hydraulic effficiency neglecting the slip\n",
+      "n=0.06#Percentage occupied by blades on circumference area\n",
+      "\n",
+      "#calculations\n",
+      "A=(pi/4)*(Dp**2)#Area of flow in pipe in m**2\n",
+      "V=Q/A#Velocity in the pipes in m/s\n",
+      "OL=3*V**2/(2*g)#Other loses in the pipes in m\n",
+      "TL=(4*f*L*V**2/(2*g*Dp))+(OL)#Total loses in a pipe in m\n",
+      "TH=TL+H#Total required head in m\n",
+      "N=(Ns*((g*TH)**(3/4)))/((Q)**(1/2))#The speed of the pump in rev/s\n",
+      "from sympy import symbols, solve\n",
+      "from sympy import N as NN\n",
+      "D = symbols('D')\n",
+      "Ao=pi*WD*(1-n)*D**2#Flow area perpendicular to impeller outlet periphery \n",
+      "Cr2=Q/Ao#Flow velocity through impeller at outlet in m/s\n",
+      "U2=pi*D*N#Outlet tangential impeller velocity in m/s\n",
+      "Cx2=(g*TH)/(U2*nh)#Absolute whirl velocity in m/s\n",
+      "expr = tan(b22*pi/180)-(Cr2/(Cx2-U2)) # polynomial of D\n",
+      "D = solve(expr, D) # discarding -ve values \n",
+      "D = D[2] # Now discard imaginary part as negligible(in powers of e**-23)\n",
+      "D = NN(abs(D),3) # in meters # rounding off\n",
+      "#output\n",
+      "print 'The pump impeller diameter is %3.3f m'%(D)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "The pump impeller diameter is 0.214 m\n"
+       ]
+      }
+     ],
+     "prompt_number": 12
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 8.13 Page 370"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "N=2875#Speed of the pump in rpm \n",
+      "Q=57.2/3600#Discharge of the pump in m**3/s\n",
+      "Hm=42.1#Total head developed by the pump in m\n",
+      "d=1000#Density of the water in kg/m**3\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "n=0.76#Efficiency of the pump\n",
+      "\n",
+      "#calculations\n",
+      "Ns=(N*Q**(1/2))/(Hm**(3/4))#Specific speed of the pump \n",
+      "P=((d*g*Q*Hm)/n)*10**-3#Power input in kW\n",
+      "\n",
+      "#calculations\n",
+      "print '(a)Specific speed of the pump is %3.f\\n(b)Power input is %3.3f kW'%(Ns,P)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Specific speed of the pump is  22\n",
+        "(b)Power input is 8.634 kW\n"
+       ]
+      }
+     ],
+     "prompt_number": 13
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 8.14 Page 371"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import ceil\n",
+      "#input data\n",
+      "D1=0.6#Inlet impeller diameter in m\n",
+      "D2=1.2#Outlet impeller diameter in m\n",
+      "Cr2=2.5#Radial flow velocity in m/s\n",
+      "N=200#Running speed of the pump in rpm\n",
+      "Q=1.88#Discharge of the pump in m**3/s\n",
+      "Hm=6#Head which the pump has to overcome in m\n",
+      "b22=26#Vane angle at exit at tangent to impeller in degree\n",
+      "d=1000#Density of the water in kg/m**3\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "\n",
+      "#calculations\n",
+      "U2=(3.1415*D2*N)/60#Outlet tangential impeller velocity in m/s\n",
+      "Wx2=Cr2/tan(b22*pi/180)#Exit relative velocity in m/s\n",
+      "Cx2=U2-Wx2#Absolute whirl velocity in m/s\n",
+      "nm=(Hm/(U2*Cx2/g))#Manometric efficiency \n",
+      "Nls=((2*g*Hm*60**2)/((3.1415**2)*((1.2**2)-(0.6**2))))**(1/2)#Least starting speed of the pump in rpm\n",
+      "\n",
+      "#output\n",
+      "print '(1)Manometric efficiency is %0.1f %%\\n(2)Least speed to start the pump is %3.2f rpm, rounding off = %0.f rpm'%(nm*100,Nls, ceil(Nls))"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(1)Manometric efficiency is 63.0 %\n",
+        "(2)Least speed to start the pump is 199.40 rpm, rounding off = 200 rpm\n"
+       ]
+      }
+     ],
+     "prompt_number": 14
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 8.15 Page 372"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "D2=1.25#External diameter of the impeller in m\n",
+      "D1=0.5#Internal diameter of the impeller in m\n",
+      "Q=2#Discharge of the pump in m**3/s\n",
+      "Hm=16#Head over which pump has to operate in m\n",
+      "N=300#Running speed of the pump in rpm\n",
+      "b22=30#Angle at which vanes are curved back in degree\n",
+      "Cr1=2.5#Flow velocity through impeller at inlet in m/s\n",
+      "Cr2=Cr1#Flow velocity through impeller at outlet in m/s\n",
+      "d=1000#Density of the water in kg/m**3\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "\n",
+      "#calculations\n",
+      "U2=(3.1415*D2*N)/60#Outlet tangential impeller velocity in m/s\n",
+      "Wx2=Cr2/tan(b22*pi/180)#Exit relative velocity in m/s\n",
+      "Cx2=U2-Wx2#Absolute whirl velocity in m/s\n",
+      "nm=(Hm*g)/(U2*Cx2)#Manometric or hydraulic efficiency\n",
+      "m=d*Q#Mass flow rate of water in kg/s\n",
+      "W=m*U2*Cx2*10**-3#Fluid power developed by the impeller in kW\n",
+      "Ps=W#Power required by the pump in kW neglecting mechanical loses\n",
+      "Nls=((2*g*Hm)/(((3.1415/60)**2)*(D2**2-D1**2)))**(1/2)#Minimum starting speed of the pump in rpm\n",
+      "\n",
+      "#output\n",
+      "print '(a)Manometric or hydraulic efficiency is %0.1f %% \\n(b)Power required by the pump is %3.2f kW\\n(c)Minimum starting speed of the pump is %3.1f rpm'%(nm*100,Ps,Nls)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Manometric or hydraulic efficiency is 52.2 % \n",
+        "(b)Power required by the pump is 600.98 kW\n",
+        "(c)Minimum starting speed of the pump is 295.4 rpm\n"
+       ]
+      }
+     ],
+     "prompt_number": 15
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 8.16 Page 373"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "n=3#Number of stages \n",
+      "D2=0.4#Outlet impeller diameter in m\n",
+      "b2=0.02#Outlet impeller width in m\n",
+      "b22=45#Backward vanes angle at outlet in degree\n",
+      "dA=0.1#Reduction in circumferential area\n",
+      "nm=0.9#Manometric efficiency of the pump\n",
+      "Q=0.05#Discharge of the pump in m**3/s\n",
+      "N=1000#Running speed of the pump in rpm\n",
+      "n0=0.8#Overall efficiency of the pump\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "d=1000#Density of water in kg/m**3\n",
+      "\n",
+      "#calculations\n",
+      "A2=(1-dA)*3.1415*D2*b2#Area of flow at outlet in m**2\n",
+      "Cr2=Q/A2#Flow velocity through impeller at outlet in m/s\n",
+      "U2=(3.1415*D2*N)/60#Outlet impeller tangential velocity in m/s\n",
+      "Wx2=Cr2#Exit relative velocity in m/s as tand(b22)=1\n",
+      "Cx2=U2-Wx2#Absolute whirl velocity in m/s\n",
+      "Hm=(nm*U2*Cx2)/g#Head over which pump has to operate in m\n",
+      "H=n*Hm#Total head generated by the pump in m\n",
+      "P=d*g*Q*Hm*n#Power output from the pump in W\n",
+      "Ps=P/n0*10**-3#Shaft power input in kW\n",
+      "\n",
+      "#output\n",
+      "print '(1)The head generated by the pump is %3.2f m\\n(2)Shaft power input is %3.3f kW'%(H,Ps)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(1)The head generated by the pump is 107.98 m\n",
+        "(2)Shaft power input is 66.205 kW\n"
+       ]
+      }
+     ],
+     "prompt_number": 16
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 8.17 Page 374"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "H=156#Total head operated by the pumps in m\n",
+      "N=1000#Running speed of the pump in rpm\n",
+      "Ns=20#Specific speed of each pump \n",
+      "Q=0.150#Discharge of the pump in m**3/s\n",
+      "\n",
+      "#calculations\n",
+      "Hm=((N*(Q)**(1/2))/(Ns))**(4/3)#Head developed by each pump in m\n",
+      "n=H/Hm#Number of pumps\n",
+      "\n",
+      "#output\n",
+      "print 'The number of pumps are %3.f'%(n)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "The number of pumps are   3\n"
+       ]
+      }
+     ],
+     "prompt_number": 17
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 8.18 Page 375"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "Q1=120#Discharge of each of the multi stage pump in parallel in first case in m**3/s\n",
+      "Q2=450#Discharge of the multi stage pump in second case in m**3/s\n",
+      "H1=16#Head of each stage in first case in m\n",
+      "D1=0.15#Diameter of impeller in first case in m\n",
+      "H=140#Total head developed by all pumps in second case in m\n",
+      "N1=1500#Running speed of the pump in rpm in first case\n",
+      "N2=1200#Running speed of the pump in rpm in second case\n",
+      "#calculations\n",
+      "H2=H1*((Q2/Q1)*((N2/N1)**2))**(4/6)#Head of each stage in second case in m\n",
+      "n=H/H2#Number of stages in second case \n",
+      "D2=D1*(((N1/N2)**(2))*(H2/H1))**(1/2)#Diameter of impeller in second case in m\n",
+      "\n",
+      "#output\n",
+      "print '(a)number of stages required is %3.f\\n(b)Diameter of impeller in the second case is %3.2f m or %0.f mm'%(n,D2, D2*1000)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)number of stages required is   5\n",
+        "(b)Diameter of impeller in the second case is 0.25 m or 251 mm\n"
+       ]
+      }
+     ],
+     "prompt_number": 18
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 8.19 Page 376"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "H=36#Initial total head of the pump in m\n",
+      "Q1=0.05#Initial discharge of the pump in m**3/s\n",
+      "H2=3.5#Sum of static pressure and velocity head at inlet in m\n",
+      "P01=0.75#Atmospheric pressure initially in m of Hg\n",
+      "Pvap1=1.8*10**3#Vapour pressure of water initially in Pa\n",
+      "Pvap2=830#Vapour pressure of water finanlly in Pa\n",
+      "P02=0.62#Atmospheric pressure finally in m of Hg\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "dW=1000#Density of water in kg/m**3\n",
+      "dHg=13.6#Density of mercury in kg/m**3\n",
+      "\n",
+      "#calculations\n",
+      "NPSH=H2-((Pvap1)/(dW*g))#Net positive suction head in m\n",
+      "s=NPSH/H#Cavitation parameter when pump dvelops same total head and discharge \n",
+      "dH1=(P01*dHg)-(s*H)-(Pvap1/(dW*g))#The height reduced in initial condition above supply in m\n",
+      "dH2=(P02*dHg)-(s*H)-(Pvap2/(dW*g))#The height reduced in final condition above supply in m\n",
+      "Z=dH1-dH2#The total height which the pump must be lowered at new location in m\n",
+      "\n",
+      "#output\n",
+      "print '(a)The cavitation parameter is %3.4f\\n(b)\\n    The height reduced in initial condition above supply is %3.1f m\\n    The height reduced in final condition above supply is %3.2f m\\n    The total height which the pump must be lowered at new location is %3.2f m'%(s,dH1,dH2,Z)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The cavitation parameter is 0.0921\n",
+        "(b)\n",
+        "    The height reduced in initial condition above supply is 6.7 m\n",
+        "    The height reduced in final condition above supply is 5.03 m\n",
+        "    The total height which the pump must be lowered at new location is 1.67 m\n"
+       ]
+      }
+     ],
+     "prompt_number": 19
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 8.20 Page 377"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import degrees, atan\n",
+      "#input data\n",
+      "Dt=1#Impeller outlet diameter in m\n",
+      "Dh=0.5#Diameter of the boss in m\n",
+      "Ns=38#Specific speed of the pump \n",
+      "Ca=2#Velocity of the flow in m/s\n",
+      "H=6#Head which the pump has to drive in m\n",
+      "\n",
+      "#calculations\n",
+      "A=(3.1415/4)*(Dt**2-Dh**2)#Area of flow in m**2\n",
+      "Q=A*Ca#Discharge of the pump in m**3/s\n",
+      "N=(Ns*H**(3/4))/(Q**(1/2))#Pump speed in rpm\n",
+      "U1=(3.1415*Dh*N)/60#Blade inlet speed in m/s\n",
+      "b1=degrees(atan(Ca/U1))#Vane angle at the entry of the pump when the flow is axial at inlet in degree\n",
+      "\n",
+      "#output\n",
+      "print '(a)Pump speed is %0.2f rpm\\n(b)Vane angle at the entry of the pump when the flow is axial at inlet is %3.2f degree'%(N,b1)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Pump speed is 134.22 rpm\n",
+        "(b)Vane angle at the entry of the pump when the flow is axial at inlet is 29.65 degree\n"
+       ]
+      }
+     ],
+     "prompt_number": 20
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 8.21 Page 378"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "Q=0.180#Discharge of the pump in m**3/s\n",
+      "H=2#Head developed by the pump in m\n",
+      "Ns=250#Specific speed of the pump \n",
+      "SR=2.4#Speed ratio of the pump\n",
+      "FR=0.5#Flow ratio of the pump\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "\n",
+      "#calculations\n",
+      "N=(Ns*(H**(3/4)))/(Q**(1/2))#Pump speed in rpm\n",
+      "U=SR*(2*g*H)**(1/2)#Peripheral velocity in m/s\n",
+      "D=(60*U)/(3.1415*N)#Runner diameter of the pump in m\n",
+      "Ca=FR*(2*g*H)**(1/2)#Velocity of flow in m/s\n",
+      "Dh=((D**2)-(Q*4/(Ca*3.14)))**(1/2)#Boss diameter of the pump in m\n",
+      "\n",
+      "#output\n",
+      "print '(a)Pump speed is %3.i rpm\\n(b)Runner diameter of the pump is %3.2f m\\n(c)Boss diameter of the pump is %3.2f m\\n'%(N,D,Dh)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Pump speed is 991 rpm\n",
+        "(b)Runner diameter of the pump is 0.29 m\n",
+        "(c)Boss diameter of the pump is 0.10 m\n",
+        "\n"
+       ]
+      }
+     ],
+     "prompt_number": 21
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 8.22 Page 379"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "Hs=2.5#Height of the pipe above suction reservoir in m\n",
+      "H1=18#Height of the pipe below supply reservoir in m\n",
+      "H=2.7#Total height through which the pump lifts water in m\n",
+      "Q1=2.75#Discharge of water used from supply reservoir in l/s\n",
+      "Qt=7.51#Discharge of water totally delivered in l/s\n",
+      "\n",
+      "#calculations\n",
+      "Hd=H-Hs#Height of the pipe from discharge reservoir in m\n",
+      "Qs=Qt-Q1#Discharge of water in delivery reservoir in l/s\n",
+      "nj=(Qs/Q1)*((Hs+Hd)/(H1-Hd))#Jet pump efficiency \n",
+      "\n",
+      "#output\n",
+      "print 'The efficiency of the jet pump is %0.1f'%(nj*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "The efficiency of the jet pump is 26.3\n"
+       ]
+      }
+     ],
+     "prompt_number": 22
+    }
+   ],
+   "metadata": {}
+  }
+ ]
+}
\ No newline at end of file
diff --git a/Turbomachines_by_A._V._Arasu/Ch9.ipynb b/Turbomachines_by_A._V._Arasu/Ch9.ipynb
new file mode 100644
index 00000000..9ea40cea
--- /dev/null
+++ b/Turbomachines_by_A._V._Arasu/Ch9.ipynb
@@ -0,0 +1,1077 @@
+{
+ "metadata": {
+  "name": "",
+  "signature": "sha256:52c2219fbd43444e9f10668aa35432419392cd1b075ad84ee07b92a8e31571e1"
+ },
+ "nbformat": 3,
+ "nbformat_minor": 0,
+ "worksheets": [
+  {
+   "cells": [
+    {
+     "cell_type": "heading",
+     "level": 1,
+     "metadata": {},
+     "source": [
+      "Chapter 9 - Hydraulic Turbines"
+     ]
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 9.1 Page 406"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from __future__ import division\n",
+      "\n",
+      "#input data\n",
+      "H=91.5#Head of the pelton wheel at inlet in m\n",
+      "Q=0.04#Discharge of the pelton wheel in m**3/s\n",
+      "N=720#Rotating speed of the wheel in rpm\n",
+      "Cv=0.98#Velocity coefficient of the nozzle \n",
+      "n0=0.8#Efficiency of the wheel\n",
+      "UC1=0.46#Ratio of bucket speed to jet speed\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",
+      "P=dw*g*H*Q*n0*10**-3#Power developed in kw\n",
+      "C1=Cv*(2*g*H)**(1/2)#Jet speed in m/s\n",
+      "U=UC1*C1#Wheel speed in m/s\n",
+      "w=(2*3.1415*N)/60#Angular velocity of the wheel in rad/s\n",
+      "D=(2*U)/w#Diameter of the wheel in m\n",
+      "A=Q/C1#Jet area in m**2\n",
+      "d=((4*A)/3.1415)**(1/2)#Jet diameter in m\n",
+      "Dd=D/d#Wheel to jet diameter ratio at centre line of the buckets\n",
+      "Nsp=((1/(g*H))**(5/4))*(((P*10**3)/dw)**(1/2))*(N/60)*2*3.1415#Dimensionless power specific speed in rad\n",
+      "\n",
+      "#output\n",
+      "print '(a)Wheel-to-jet diameter ratio at the centre line of the buckets is %3.1f \\n(b)\\n    The jet speed of the wheel is %3.2f m/s\\n    Wheel speed is %3.1f m/s\\n(c)Dimensionless power specific speed is %3.3f rad'%(Dd,C1,U,Nsp)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Wheel-to-jet diameter ratio at the centre line of the buckets is 14.5 \n",
+        "(b)\n",
+        "    The jet speed of the wheel is 41.52 m/s\n",
+        "    Wheel speed is 19.1 m/s\n",
+        "(c)Dimensionless power specific speed is 0.082 rad\n"
+       ]
+      }
+     ],
+     "prompt_number": 1
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 9.2 Page 407"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "H=500#Head over which pelton wheel works in m\n",
+      "P=13000#Power which pelton wheel produces in kW\n",
+      "N=430#Speed of operation of pelton wheel in rpm\n",
+      "n0=0.85#Efficiency of the wheel \n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "dw=1000#Density of water in kg/m**3\n",
+      "Cv=0.98#Veloity coefficient\n",
+      "UC=0.46#Speed ratio\n",
+      "\n",
+      "#calculations\n",
+      "Q=(P*10**3)/(dw*g*H*n0)#Discharge of the turbine in m**3/s\n",
+      "C=Cv*(2*g*H)**(1/2)#Jet speed in m/s\n",
+      "U=UC*C#Wheel speed in m/s\n",
+      "D=(U*60)/(3.1415*N)#Wheel diameter in m\n",
+      "d=((Q/C)*(4/3.1415))**(1/2)#Diameter of the nozzle in m\n",
+      "\n",
+      "#output\n",
+      "print '(a)Discharge of the turbine is %3.2f m**3/s\\n(b)Diameter of the wheel is %3.2f m\\n(c)Diameter of the nozzle is %3.3f m'%(Q,D,d)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Discharge of the turbine is 3.12 m**3/s\n",
+        "(b)Diameter of the wheel is 1.98 m\n",
+        "(c)Diameter of the nozzle is 0.202 m\n"
+       ]
+      }
+     ],
+     "prompt_number": 2
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 9.3 Page 409"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import pi, cos\n",
+      "#input data\n",
+      "D=0.8#Mean diameter of the bucket in m\n",
+      "N=1000#Running speed of the wheel in rpm\n",
+      "H=400#Net head on the pelton wheel in m\n",
+      "Q=0.150#Discharge through the nozzle in m**3/s\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "UC1=0.46#Ratio of bucket speed to jet speed\n",
+      "dw=1000#Density of water in kg/m**3\n",
+      "a=15#Side clearance angle in degree\n",
+      "\n",
+      "#calculations\n",
+      "m=dw*Q#Mass flow rate through the nozzle in kg/s\n",
+      "U=(3.1415*D*N)/60#Wheel speed in m/s\n",
+      "C1=U/UC1#Jet speed in m/s\n",
+      "P=(1/2)*m*C1**2*(10**-3)#Power available at the nozzle in kW\n",
+      "W1=C1-U#Relative inlet fluid velocity in m/s\n",
+      "W2=W1#Relative exit fluid velocity in m/s assuming no loss of relative velocity\n",
+      "Wx2=W2*cos(a*pi/180)#Exit whirl velocity component in m/s\n",
+      "Cx2=Wx2-U#Absolute exit whirl velocity in m/s\n",
+      "Cx1=C1#Absolute inlet whirl velocity in m/s\n",
+      "Wm=U*(Cx1+Cx2)#Work done per unit mass flow rate in W/(kg/s)\n",
+      "nH=(Wm/g)/((C1**2/2)/g)#Hydrualic effciency \n",
+      "\n",
+      "#output\n",
+      "print '(a)Power available at the nozzle is %3.3f kW\\n(b)Hydraulic efficiency is %.1f %%'%(P,nH*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Power available at the nozzle is 621.867 kW\n",
+        "(b)Hydraulic efficiency is 97.7 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 3
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 9.4 Page 409"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "n=2#Number of jets \n",
+      "SP=20000*0.736#Shaft power of the wheel in kW\n",
+      "D=0.15#Diameter of each jet in m\n",
+      "H=500#Net head on the turbine in m\n",
+      "Cv=1.0#Velocity coefficient\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "d=1000#Density of water in kg/m**3\n",
+      "\n",
+      "#calculations\n",
+      "C1=Cv*(2*g*H)**(1/2)#Velocity of each jet in m/s\n",
+      "A=(3.1415/4)*D**2#Area of each jet in m**2\n",
+      "Qj=A*C1#Discharge of each jet in m**3/s\n",
+      "Q=2*Qj#Total discharge in m**3/s\n",
+      "P=d*g*Q*H*10**-3#Power at turbine inlet in kW\n",
+      "no=SP/P#Overall efficiency\n",
+      "\n",
+      "#output\n",
+      "print 'The overall efficiency of the turbine is %0.1f %%'%(no*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "The overall efficiency of the turbine is 85.7 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 4
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 9.5 Page 410"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "a=170#Jet deflection angle in degree\n",
+      "K=1-0.12#Percentage of effective relative velocity after considering friction\n",
+      "UC1=0.47#Ratio of bucket speed to jet speed\n",
+      "GH=600#Gross head on the wheel in m\n",
+      "P=1250#Actual power developed by the wheel in kW\n",
+      "Hl=48#Head loss in nozzle due to pipe friction in m\n",
+      "D=0.9#Bucket circle diameter of the wheel in m\n",
+      "ATnH=0.9#The ratio between actual and calculated hydraulic efficiency\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "dw=1000#Density of water in kg/m**3\n",
+      "Cv=0.98#Velocity coefficient\n",
+      "\n",
+      "#calculations\n",
+      "H=GH-Hl#Net head after loses at entry to nozzle in m\n",
+      "C1=Cv*(2*g*H)**(1/2)#Jet speed in m/s\n",
+      "U=UC1*C1#Wheel bucket speed in m/s\n",
+      "N=(U*60)/(3.1415*D)#Wheel rotational speed in rpm\n",
+      "Wm=U*((C1-U)*(1-(K*cos(a*pi/180))))#Work done per unit mass flow rate in W/(kg/s)\n",
+      "Tnh=Wm/(C1**2/2)#Theoretical hydraulic efficiency \n",
+      "Anh=ATnH*Tnh#Actual hydrualic effficiency\n",
+      "m2=(P*10**3)/(Anh*(1/2)*C1**2)#Mass flow rate for both the nozzles in kg/s\n",
+      "m=m2/2#Mass flow rate of each nozzle in kg/s\n",
+      "d=((4*m)/(dw*C1*3.1415))**(1/2)#Nozzle diameter in m\n",
+      "\n",
+      "#output\n",
+      "print '(a)theoretical hydraulic efficiency is %3.2f \\n(b)Wheel rotational speed is %3.f rpm\\n(c)diameter of the nozzle is %0.1f mm'%(Tnh,N,d*1000)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)theoretical hydraulic efficiency is 0.93 \n",
+        "(b)Wheel rotational speed is 1017 rpm\n",
+        "(c)diameter of the nozzle is 42.3 mm\n"
+       ]
+      }
+     ],
+     "prompt_number": 5
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 9.6 Page 413"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "H=60#Head on the pelton wheel in m\n",
+      "N=200#Speed of the pelton wheel in rpm\n",
+      "P=100#Power developed by the pelton wheel in kW\n",
+      "Cv=0.98#Velocity coefficient\n",
+      "UC1=0.45#Speed ratio \n",
+      "n0=0.85#Overall efficiency of the wheel\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",
+      "C1=Cv*(2*g*H)**(1/2)#Velocity of the jet in m/s\n",
+      "U=UC1*(2*g*H)**(1/2)#Velocity of the buckets in m/s\n",
+      "D=(60*U)/(3.1415*N)#Diameter of the wheel in m\n",
+      "Q=(P*10**3)/(dw*g*H*n0)#Discharge of the wheel in m**3/s\n",
+      "d=((4*Q)/(3.1415*C1))**(1/2)#Diameter of the jet in m\n",
+      "Z=15+(D/(2*d))+1#Number of buckets rounding off to nearest decimal as the final answer has a decimal value less than 0.5\n",
+      "w=5*d#Width of the buckets in m\n",
+      "de=1.2*d#Depth of the buckets in m\n",
+      "\n",
+      "#output\n",
+      "print '(a)Diameter of the wheel is %3.2f m\\n(b)Diameter of the jet is %3.3f m\\n(c)Number of buckets is %3.f\\n(d)Size of the buckets is \\n    width of the bucket is %3.3f m\\n    Depth of the bucket is %3.3f m'%(D,d,Z,w,de)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Diameter of the wheel is 1.47 m\n",
+        "(b)Diameter of the jet is 0.087 m\n",
+        "(c)Number of buckets is  24\n",
+        "(d)Size of the buckets is \n",
+        "    width of the bucket is 0.435 m\n",
+        "    Depth of the bucket is 0.104 m\n"
+       ]
+      }
+     ],
+     "prompt_number": 6
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 9.7 Page 414"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "N=300#Running speed of the wheel in rpm\n",
+      "H=150#OPerating head of the wheel in m\n",
+      "dD=1/12#Ratio of nozzle diameter to wheel diameter\n",
+      "Cv=0.98#Velocity coefficient\n",
+      "UC1=0.46#Speed ratio\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "dw=1000#Density of water in kg/m**3\n",
+      "n0=0.84#Overall efficiency\n",
+      "\n",
+      "#calculations\n",
+      "C1=Cv*(2*g*H)**(1/2)#Velocity of jet in m/s\n",
+      "U=UC1*(2*g*H)**(1/2)#Velocity of the wheel in m/s\n",
+      "D=(60*U)/(3.14*N)#Diameter of the wheel in m\n",
+      "d=D*dD#Diameter of the jet in m\n",
+      "Q=(3.1415/4)*(d**2)*C1#Quantity of water required in m**3/s\n",
+      "Pa=dw*g*Q*H#Power available at the nozzle in kW\n",
+      "P=n0*Pa*10**-3#Power developed in kW\n",
+      "#output\n",
+      "print '(a)Diameter of the wheel is %3.2f m\\n(b)Diameter of the jet is %3.3f m\\n(c)Quantity of water required is %3.3f m**3/s\\n(d)Power developed is %3.1f kW'%(D,d,Q,P)\n",
+      "# Answer in the textbook is wrong."
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Diameter of the wheel is 1.59 m\n",
+        "(b)Diameter of the jet is 0.132 m\n",
+        "(c)Quantity of water required is 0.733 m**3/s\n",
+        "(d)Power developed is 905.5 kW\n"
+       ]
+      }
+     ],
+     "prompt_number": 7
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 9.8 Page 415"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import tan, pi\n",
+      "#input data\n",
+      "N=1260#Rotational speed of the francis turbine in rpm\n",
+      "H=124#The net head in m\n",
+      "Q=0.5#Volume flow rate of the turbine in m**3/s\n",
+      "r1=0.6#Radius of the runner in m\n",
+      "b1=0.03#Height of the runner vanes at inlet in m\n",
+      "b11=72#Angle of inlet guide vanes in radial direction in degree\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "dw=1000#Density of water in kg/m**3\n",
+      "Cx2=0#Absolute exit whirl velocity in m/s as flow is radial at outlet\n",
+      "\n",
+      "#calculations\n",
+      "m=dw*Q#Mass flow rate in kg/s\n",
+      "T1=-m*r1#Torque by the turbine in Nm in terms of Cx1\n",
+      "A=2*3.1415*r1*b1#Area at inlet in m**2\n",
+      "Cr1=Q/A#Inlet flow velocity in m/s\n",
+      "Cx1=Cr1*tan(b11*pi/180)#Absolute inlet whirl velocity in m/s\n",
+      "T=-T1*Cx1#Torque by water on the runner in Nm\n",
+      "w=(2*3.1415*N)/60#Angular velocity of the turbine in rad/s\n",
+      "W=T*w*10**-3#Power exerted in kW\n",
+      "nH=W*10**3/(dw*g*Q*H)#Hydraulic efficiency \n",
+      "\n",
+      "#output\n",
+      "print '(a)Torque by water on the runner is -%3.f Nm\\n(b)Power exerted is %3i kW\\n(c)Hydraulic efficiency is %0.1f %%'%(T,W,nH*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Torque by water on the runner is -4082 Nm\n",
+        "(b)Power exerted is 538 kW\n",
+        "(c)Hydraulic efficiency is 88.6 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 8
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 9.9 Page 416"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import atan, degrees\n",
+      "#input data\n",
+      "n0=0.74#Overall efficiency\n",
+      "H=5.5#Net head across the turbine in m\n",
+      "P=125#Required Power output in kW\n",
+      "N=230#Speed of the runner in rpm\n",
+      "nH=(1-0.18)#Hydraulic efficiency\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "dw=1000#Density of water in kg/m**3\n",
+      "U1=0.97*(2*g*H)**(1/2)#Runner tangential velocity in m/s\n",
+      "Cr1=0.4*(2*g*H)**(1/2)#Flow velocity in m/s\n",
+      "\n",
+      "#calculations\n",
+      "Cx1=(nH*g*H)/U1#Absolute inlet whirl velocity in m/s    as flow is radial at outlet Cx2=0  in m/s\n",
+      "a11=degrees(atan(Cr1/Cx1))#Inlet guide vane angle in degree\n",
+      "b11=180+degrees(atan(Cr1/(Cx1-U1)))#Angle of inlet guide vanes in radial direction in degree\n",
+      "D1=(U1*60)/(3.1415*N)#Runner inlet diameter in m\n",
+      "Q=(P*10**3)/(n0*dw*g*H)#Flow rate in m**3/s\n",
+      "b1=Q/(3.1415*D1*Cr1)#Height of runner in m\n",
+      "\n",
+      "#output\n",
+      "print '(a)Inlet guide vane angle is %3.1f degree\\n(b)Angle of inlet guide vanes in radial direction is %3.1f degree\\n(c)Runner inlet diameter is %3.3f m\\n(d)Height of runner is %3.3f m'%(a11,b11,D1,b1)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Inlet guide vane angle is 43.4 degree\n",
+        "(b)Angle of inlet guide vanes in radial direction is 143.8 degree\n",
+        "(c)Runner inlet diameter is 0.837 m\n",
+        "(d)Height of runner is 0.287 m\n"
+       ]
+      }
+     ],
+     "prompt_number": 9
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 9.10 Page 418"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "D=1.4#Diameter of the turbine in m\n",
+      "N=430#Speed of the turbine in rpm\n",
+      "Cr1=9.5#Flow velocity without shock at runner in m/s\n",
+      "C2=7#Absolute velocity at the exit without whirl in /s\n",
+      "dSPH=62#Difference between the sum of static and potential heads at entrance to runner and at exit from runner in m\n",
+      "W=12250#Power given to runner in kW\n",
+      "Q=12#Flow rate of water from the turbine in m**3/s\n",
+      "H=115#Net head from the turbine in m\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",
+      "U1=(3.1415*D*N)/60#Runner tip speed in m/s\n",
+      "Cx1=(W*10**3)/(dw*Q*U1)#Absolute inlet velocity in m/s    as flow is radial at outlet Cx2=0  in m/s as Cx2=0 as zero whirl at outlet\n",
+      "a1=degrees(atan(Cr1/Cx1))#Guide vane angle in degree\n",
+      "C1=(Cr1**2+Cx1**2)**(1/2)#Inlet velocity in  m/s\n",
+      "b1=degrees(atan(Cr1/(Cx1-U1)))#Runner blade entry angle in degree\n",
+      "dHr=dSPH+(((C1**2)-(C2**2))/(2*g))-(U1*Cx1/g)#Loss of head in the runner in m\n",
+      "\n",
+      "#output\n",
+      "print '(a)\\n    (1)Guide vane angle at inlet is %3.1f degree\\n    (2)Inlet absolute velocity of water at entry to runner is %3.1f m/s\\n(b)Runner blade entry angle is %3.1f degree\\n(c)Total Loss of head in the runner is %3.2f m'%(a1,C1,b1,dHr)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)\n",
+        "    (1)Guide vane angle at inlet is 16.3 degree\n",
+        "    (2)Inlet absolute velocity of water at entry to runner is 33.8 m/s\n",
+        "(b)Runner blade entry angle is 84.8 degree\n",
+        "(c)Total Loss of head in the runner is 13.50 m\n"
+       ]
+      }
+     ],
+     "prompt_number": 10
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 9.11 Page 420"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from math import sin, tan, degrees\n",
+      "#input data\n",
+      "D1=0.9#External diameter of the turbine in m\n",
+      "D2=0.45#Internal diameter of the turbine in m\n",
+      "N=200#Speed of turbine running in rpm\n",
+      "b1=0.2#Width of turbine at inlet in m\n",
+      "Cr1=1.8#Velocity of flow through runner at inlet in m/s\n",
+      "Cr2=Cr1#Velocity of flow through runner at outlet in m/s\n",
+      "a11=10#Guide blade angle to the tangent of the wheel in degree\n",
+      "a22=90#Discharge angle at outlet of turbine in degree\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",
+      "C1=Cr1/sin(a11*pi/180)#Absolute velocity of water at inlet of runner in m/s\n",
+      "Cx1=Cr1/tan(a11*pi/180)#Velocity of whirl at inlet in m/s\n",
+      "U1=(3.1415*D1*N)/60#Runner tip speed at inlet in m/s\n",
+      "Wx1=Cx1-U1#Inlet whirl velocity component in m/s\n",
+      "W1=(Wx1**2+Cr1**2)**(1/2)#Relative velocity at inlet in m/s\n",
+      "b11=degrees(atan(Cr1/Wx1))#Runner blade entry angle in degree\n",
+      "U2=(3.1415*D2*N)/60#Runner tip speed at exit in m/s\n",
+      "b22=degrees(atan(Cr2/U2))#Runner blade exit angle in degree\n",
+      "b2=D1*b1/D2#Width of runner at outlet in m\n",
+      "Q=3.1415*D1*b1*Cr1#Discharge of water in turbine in m**3/s\n",
+      "m=dw*Q#Mass of water flowing through runner per second in kg/s\n",
+      "V2=Cr2#Velocity of water at exit in m/s \n",
+      "H=(U1*Cx1/g)+(V2**2/(2*g))#Head at the turbine inlet in m\n",
+      "W=m*U1*Cx1*10**-3#Power developed in kW\n",
+      "nH=(U1*Cx1/(g*H))#Hydraulic efficiency\n",
+      "\n",
+      "#output\n",
+      "print '(a)Absolute velocity of water at inlet of runner is %3.3f m/s\\n(b)Velocity of whirl at inlet is %3.3f m/s\\n(c)Relative velocity at inlet is %3.3f m/s\\n(d)\\n    Runner blade entry angle is %3.2f degree\\n    Runner blade exit angle is %3.2f degree\\n(e)Width of runner at outlet is %3.1f m\\n(f)Mass of water flowing through runner per second is %3.f kg/s\\n(g)Head at the turbine inlet is %3.3f m\\n(h)Power developed is %3.3f kW\\n(i)Hydraulic efficiency is %0.2f %%'%(C1,Cx1,W1,b11,b22,b2,m,H,W,nH*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Absolute velocity of water at inlet of runner is 10.366 m/s\n",
+        "(b)Velocity of whirl at inlet is 10.208 m/s\n",
+        "(c)Relative velocity at inlet is 1.963 m/s\n",
+        "(d)\n",
+        "    Runner blade entry angle is 66.47 degree\n",
+        "    Runner blade exit angle is 20.91 degree\n",
+        "(e)Width of runner at outlet is 0.4 m\n",
+        "(f)Mass of water flowing through runner per second is 1018 kg/s\n",
+        "(g)Head at the turbine inlet is 9.972 m\n",
+        "(h)Power developed is 97.925 kW\n",
+        "(i)Hydraulic efficiency is 98.34 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 11
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 9.12 Page 423"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "P=330#Power output from the turbine is kW\n",
+      "H=70#Head of operating turbine in m\n",
+      "N=750#Speed of the turbine in rpm\n",
+      "nH=0.94#Hydraulic efficiency\n",
+      "n0=0.85#Overall efficiency\n",
+      "FR=0.15#Flow ratio \n",
+      "BR=0.1#Breadth ratio\n",
+      "D1D2=2#Ratio inner and outer diameter of runner\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",
+      "Cr1=FR*(2*g*H)**(1/2)#Flow velocity at inlet in m/s\n",
+      "Q=(P*10**3)/(dw*g*H*n0)#Discharge at outlet in m**3/s\n",
+      "D1=(Q/(nH*3.1415*BR*Cr1))**(1/2)#Runner inlet diameter in m\n",
+      "b1=BR*D1#Height of the runner vanes at inlet in m\n",
+      "U1=(3.1415*D1*N)/60#Runner tip speed at inlet in m/s\n",
+      "Cx1=(nH*g*H)/(U1)#Velocity of whirl at inlet in m/s\n",
+      "a11=degrees(atan(Cr1/Cx1))#Guide blade angle in degree\n",
+      "b11=degrees(atan(Cr1/(Cx1-U1)))#Runner vane angle at inlet in degree\n",
+      "D2=D1/D1D2#Runner outlet diameter in m\n",
+      "U2=(3.1415*D2*N)/60#Runner tip speed at outlet in m/s\n",
+      "Cr2=Cr1#Flow velocity at outlet in m/s\n",
+      "b22=degrees(atan(Cr2/U2))#Runner vane angle at outlet in degree\n",
+      "b2=D1*b1/D2#Width at outlet in m\n",
+      "\n",
+      "#output\n",
+      "print '(a)Flow velocity at inlet is %3.2f m/s\\n(b)Discharge at outlet is %3.3f m**3/s\\n(c)Runner inlet diameter is %3.3f m\\n(d)Height of the runner vanes at inlet is %3.4f m\\n(e)Guide blade angle is %3.2f degree\\n(f)    Runner vane angle at inlet is %3.2f degree\\n       Runner vane angle at outlet is %3.2f degree\\n(g)Runner outlet diameter is %3.4f m\\n(h)Width at outlet is %3.4f m\\n(i)Runner tip speed at inlet is %3.2f m/s\\n(j)Velocity of whirl at inlet is %3.f m/s'%(Cr1,Q,D1,b1,a11,b11,b22,D2,b2,U1,Cx1)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Flow velocity at inlet is 5.56 m/s\n",
+        "(b)Discharge at outlet is 0.565 m**3/s\n",
+        "(c)Runner inlet diameter is 0.587 m\n",
+        "(d)Height of the runner vanes at inlet is 0.0587 m\n",
+        "(e)Guide blade angle is 11.23 degree\n",
+        "(f)    Runner vane angle at inlet is 48.23 degree\n",
+        "       Runner vane angle at outlet is 25.75 degree\n",
+        "(g)Runner outlet diameter is 0.2934 m\n",
+        "(h)Width at outlet is 0.1174 m\n",
+        "(i)Runner tip speed at inlet is 23.05 m/s\n",
+        "(j)Velocity of whirl at inlet is  28 m/s\n"
+       ]
+      }
+     ],
+     "prompt_number": 12
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 9.13 Page 424"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "H=30#Working head of the turbine in m\n",
+      "D1=1.2#Inlet wheel diameter in m\n",
+      "D2=0.6#Outlet wheel diameter in m\n",
+      "b11=90#Vane angle at entrance in degree\n",
+      "a11=15#Guide blade angle in degree\n",
+      "Cx2=0#Velocity of whirl at inlet in m/s\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",
+      "U11=1/tan(a11*pi/180)#Runner tip speed at inlet in m/s in terms of Cr1\n",
+      "Cr1=(H/((U11**2/g)+(1/(2*g))))**(1/2)#Flow velocity at inlet in m/s\n",
+      "Cr2=Cr1#Flow velocity at outlet in m/s\n",
+      "U1=Cr1*U11#Runner tip speed at inlet in m/s  \n",
+      "N=(60*U1)/(3.1415*D1)#Speed of the wheel in rpm\n",
+      "U2=(3.1415*D2*N)/60#Runner tip speed at inlet in m/s \n",
+      "b22=degrees(atan(Cr2/U2))#Vane angle at exit in degree\n",
+      "\n",
+      "#output\n",
+      "print '(a)Speed of the wheel is %3.2f rpm\\n(b)Vane angle at exit is %3.2f degree'%(N,b22)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Speed of the wheel is 268.27 rpm\n",
+        "(b)Vane angle at exit is 28.19 degree\n"
+       ]
+      }
+     ],
+     "prompt_number": 13
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 9.14 Page 425"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "D1=0.6#Internal runner diameter in m\n",
+      "D2=1.2#External runner diameter in m\n",
+      "a11=15#Guide blade angle in degree\n",
+      "Cr1=4#Flow velocity at inlet in m/s\n",
+      "Cr2=Cr1#Flow velocity at outlet in m/s\n",
+      "N=200#Speed of the turbine in rpm\n",
+      "H=10#Head of the turbine in m\n",
+      "a22=90#Discharge angle at outlet in degree\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",
+      "U1=(3.1415*D1*N)/60#Runner tip speed at inlet in m/s \n",
+      "U2=(3.1415*D2*N)/60#Runner tip speed at outlet in m/s \n",
+      "Cx1=Cr1/tan(a11*pi/180)#Velocity of whirl at inlet in m/s\n",
+      "Wx1=Cx1-U1#Inlet whirl velocity component in m/s\n",
+      "b11=degrees(atan(Cr1/Wx1))#Vane angle at entrance in degree\n",
+      "b22=degrees(atan(Cr2/U2))#Vane angle at exit in degree\n",
+      "Wm=U1*Cx1#Work one per unit mass flow rate in W/(kg/s)     as Cx2=0 in m/s\n",
+      "nH=(U1*Cx1/(g*H))#Hydraulic efficiency \n",
+      "\n",
+      "#output\n",
+      "print '(a)\\n    Inlet vane angle is %3.2f degree\\n    Outlet vane angle is %3.2f degree\\n(b)Work done by the water on the runner per kg of water is %3.2f W/(kg/s)\\n(c)Hydraulic efficiency is %0.2f %%'%(b11,b22,Wm,nH*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)\n",
+        "    Inlet vane angle is 24.83 degree\n",
+        "    Outlet vane angle is 17.66 degree\n",
+        "(b)Work done by the water on the runner per kg of water is 93.79 W/(kg/s)\n",
+        "(c)Hydraulic efficiency is 95.61 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 14
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 9.15 Page 427"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "H=23#Net head across the turbine in m\n",
+      "N=150#Speed of the turbine in rpm\n",
+      "P=23#Power developed by the turbine in MW\n",
+      "D=4.75#Blade tip diameter in m\n",
+      "d=2#Blade hub diameter in m\n",
+      "nH=0.93#Hydraulic efficiency\n",
+      "n0=0.85#Overall efficiency\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",
+      "dm=(D+d)/2#Mean diameter of the turbine in m\n",
+      "Pa=(P*10**6)/n0#Power available in MW\n",
+      "Q=(Pa/(dw*g*H))#Flow rate in the turbine in m**3/s\n",
+      "Um=(3.1415*dm*N)/60#Rotor speed at mean diameter in m/s\n",
+      "Pr=Pa*nH*10**-6#Power given to runner in MW\n",
+      "Cx1=Pr*10**6/(dw*Q*Um)#Velocity of whirl at inlet in m/s    as Cx2=0 in m/s\n",
+      "Ca=Q/((3.1415/4)*(D**2-d**2))#Axial velocity in m/s\n",
+      "b11=180-degrees(atan(Ca/(Um-Cx1)))#Inlet blade angle in degree\n",
+      "Wx2=Um#Outlet whirl velocity component in m/s\n",
+      "b22=degrees(atan(Ca/Wx2))#Outlet blade angle in degree\n",
+      "\n",
+      "#output\n",
+      "print '(a)The inlet blade angle at mean radius is %3.1f degree\\n(b)The outlet blade angle at mean radius is %3.1f degree'%(b11,b22)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)The inlet blade angle at mean radius is 156.1 degree\n",
+        "(b)The outlet blade angle at mean radius is 17.2 degree\n"
+       ]
+      }
+     ],
+     "prompt_number": 15
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 9.16 Page 429"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "P=9100#Power developed by the turbine in kW\n",
+      "H=5.6#Net head available at the turbine in m\n",
+      "SR=2.09#Speed ratio\n",
+      "FR=0.68#Flow ratio\n",
+      "n0=0.86#Overall effiiciency of the turbine\n",
+      "g=9.81#Acceleration due to gravity in m/s**2\n",
+      "dw=1000#Density of water in kg/m**3\n",
+      "DbD=1/3#Ratio of diameter of the boss to diameter of the runner\n",
+      "\n",
+      "#calculations\n",
+      "U1=SR*(2*g*H)**(1/2)#Runner tip speed at inlet in m/s\n",
+      "Cr1=FR*(2*g*H)**(1/2)#Flow velocity at inlet in m/s\n",
+      "Q=(P*10**3)/(n0*dw*g*H)#Discharge through the turbine in m**3/s\n",
+      "D=(Q*4/(3.1415*Cr1*((1**2)-(DbD**2))))**(1/2)#Diameter of the runner in m\n",
+      "N=(U1*60)/(3.1415*D)#Speed of the the turbine in rpm\n",
+      "Ns=(N*(P)**(1/2))/(H)**(5/4)#Specific speed \n",
+      "#output\n",
+      "print '(a)Diameter of the runner of the turbine is %3.2f m\\n(b)Speed of the turbine is %3.1f rpm\\n(c)The specific speed is %3.2f'%(D,N,Ns)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Diameter of the runner of the turbine is 6.22 m\n",
+        "(b)Speed of the turbine is 67.3 rpm\n",
+        "(c)The specific speed is 744.71\n"
+       ]
+      }
+     ],
+     "prompt_number": 16
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 9.17 Page 430"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "H=20#Head developed over the turbine in m\n",
+      "P=11800#Power developed by turbine in kW\n",
+      "D=3.5#Outer diameter of the runner in m\n",
+      "Db=1.75#Hub diameter in m\n",
+      "a11=35#Guide blade angle in degree \n",
+      "nH=0.88#Hydraulic efficiency \n",
+      "n0=0.84#Overall efficiency\n",
+      "Cx2=0#Velocity of whirl at outlet in m/s\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",
+      "Q=(P*10**3)/(n0*g*H*dw)#Discharge of turbine in m**3/s\n",
+      "Cr1=Q/((3.1415/4)*(D**2-Db**2))#Flow velocity at inlet in m/s\n",
+      "Cx1=Cr1/tan(a11*pi/180)#Velocity of whirl at inlet in m/s\n",
+      "U1=(nH*H*g)/(Cx1)#Runner tip speed at inlet in m/s\n",
+      "Wx1=U1-Cx1#Inlet whirl velocity component in m/s\n",
+      "b11=180-degrees(atan(Cr1/-Wx1))#Runner inlet angle in degree\n",
+      "Cr2=Cr1#Flow velocity at outlet in m/s      for a kaplan turbine\n",
+      "U2=U1#Runner tip speed at outlet in m/s     for a kaplan turbine\n",
+      "b22=degrees(atan(Cr2/U2))#Runner outlet angle in degree \n",
+      "N=(U1*60)/(3.1415*D)#The speed of the turbine in rpm\n",
+      "\n",
+      "#output\n",
+      "print '(1)\\n    (a)The runner inlet angle is %3.2f degree\\n    (b)The runner outlet angle is %3.1f degree\\n(2)The speed of the turbine is %3.2f rpm'%(b11,b22,N)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(1)\n",
+        "    (a)The runner inlet angle is 101.33 degree\n",
+        "    (b)The runner outlet angle is 39.2 degree\n",
+        "(2)The speed of the turbine is 66.49 rpm\n"
+       ]
+      }
+     ],
+     "prompt_number": 17
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 9.18 Page 432"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "N=50#Speed of the turbine in rpm\n",
+      "d=6#Runner diameter of the turbine in m\n",
+      "Ae=20#Effective area of flow in m**2\n",
+      "b11=150#The angle of the runner blades at inlet in degree\n",
+      "b22=20#The angle of the runner blade at outlet in degree\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",
+      "U1=(3.141*d*N)/60#Runner tip speed at inlet in m/s\n",
+      "U2=U1#Runner tip speed at outlet in m/s\n",
+      "Cr2=U2*tan(b22*pi/180)#Flow velocity at outlet in m/s\n",
+      "Cr1=Cr2#Flow velocity at inlet in m/s\n",
+      "Q=Ae*Cr1#Discharge by the  turbine in m**3/s\n",
+      "Cx1=U1-(Cr1/(tan((180-b11)*pi/180)))#Velocity of whirl at inlet in m/s\n",
+      "P=dw*g*Q*(U1*Cx1/g)*10**-3#Theoretical Power developed in kW\n",
+      "C2=Cr2#Absolute outlet velocity in m/s\n",
+      "H=(U1*Cx1/g)+(C2**2/(2*g))#Net head across the turbine in m\n",
+      "nH=(U1*Cx1/g)/(H)#Hydraulic efficiency\n",
+      "\n",
+      "#output\n",
+      "print '(a)Discharge of the turbine is %3.1f m**3/s\\n(b)Theoretical Power developed is %3.2f kW\\n(c)Hydraulic efficiency is %0.2f %%'%(Q,P,nH*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Discharge of the turbine is 114.3 m**3/s\n",
+        "(b)Theoretical Power developed is 10421.35 kW\n",
+        "(c)Hydraulic efficiency is 84.80 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 18
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 9.19 Page 433"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "D=8#Outer diameter of the turbine in m\n",
+      "Db=3#Inner diameter of the turbine in m\n",
+      "P=30000#Power developed by the turbine in kW\n",
+      "nH=0.95#Hydraulic efficiency\n",
+      "N=80#Speed of the turbine in rpm\n",
+      "H=12#Head operated by the turbine in m\n",
+      "Q=300#Discharge through the runner in m**3/s\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",
+      "U1=(3.1415*D*N)/60#Runner tip speed at inlet in m/s\n",
+      "U2=U1#Runner tip speed at outlet in m/s     as flow is axial\n",
+      "Cr1=Q/((3.1415/4)*(D**2-Db**2))#Flow velocity at inlet in m/s\n",
+      "Cr2=Cr1#Flow velocity at outlet in m/s      as flow is axial\n",
+      "b22=degrees(atan(Cr2/U2))#The angle of the runner blade at outlet in degree\n",
+      "Cx1=(nH*g*H)/U1#Velocity of whirl at inlet in m/s\n",
+      "b11=180-degrees(atan(Cr1/(U1-Cx1)))#The angle of the runner blade at inlet in degree\n",
+      "nM=(P*10**3)/(dw*g*Q*(Cx1*U1/g))#Mechanical efficiency\n",
+      "n0=nM*nH#Overall efficiency\n",
+      "\n",
+      "#output\n",
+      "print '(a)Blade angle at\\n    inlet is %3.2f degree\\n    outlet is %3.2f degree\\n(b)Mechanical efficiency is %0.1f %%\\n(c)Overall efficiency is %0.1f %%'%(b11,b22,nM*100,n0*100)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Blade angle at\n",
+        "    inlet is 167.04 degree\n",
+        "    outlet is 11.71 degree\n",
+        "(b)Mechanical efficiency is 89.4 %\n",
+        "(c)Overall efficiency is 84.9 %\n"
+       ]
+      }
+     ],
+     "prompt_number": 19
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Ex 9.20 Page 434"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#input data\n",
+      "P=11500#Rated power of the turbine in kW\n",
+      "H=4.3#Average head of the turbine in m\n",
+      "n0=0.91#Overall efficiency of the turbine \n",
+      "DbD=0.3#Ratio of Diameters of runner boss and runner\n",
+      "SR=2#Speed ratio\n",
+      "FR=0.65#Flow ratio\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",
+      "U=SR*(2*g*H)**(1/2)#Runner tip speed in m/s\n",
+      "Cr=FR*(2*g*H)**(1/2)#Flow velocity in m/s\n",
+      "Q=(P*10**3)/(n0*dw*g*H)#Discharge of the turbine in m**3/s\n",
+      "D=((4*Q)/(Cr*3.1415*(1**2-DbD**2)))**(1/2)#Runner diameter in \n",
+      "N=(60*U)/(3.1415*D)#Speed of the turbine in rpm \n",
+      "\n",
+      "#output\n",
+      "print '(a)Runner diameter of the turbine is %3.2f m\\n(b)Operating speed of the turbine is %3.1f rpm'%(D,N)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "(a)Runner diameter of the turbine is 8.38 m\n",
+        "(b)Operating speed of the turbine is 41.9 rpm\n"
+       ]
+      }
+     ],
+     "prompt_number": 20
+    }
+   ],
+   "metadata": {}
+  }
+ ]
+}
\ No newline at end of file
diff --git a/Turbomachines_by_A._V._Arasu/screenshots/Ch3BladeAngPowAndPress.png b/Turbomachines_by_A._V._Arasu/screenshots/Ch3BladeAngPowAndPress.png
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diff --git a/Turbomachines_by_A._V._Arasu/screenshots/Ch4EffPress.png b/Turbomachines_by_A._V._Arasu/screenshots/Ch4EffPress.png
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diff --git a/Turbomachines_by_A._V._Arasu/screenshots/Ch5DegofReacNBladeCoeff.png b/Turbomachines_by_A._V._Arasu/screenshots/Ch5DegofReacNBladeCoeff.png
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