diff options
Diffstat (limited to 'Thermodynamics_An_Engineering_Approach/Chapter17.ipynb')
| -rwxr-xr-x | Thermodynamics_An_Engineering_Approach/Chapter17.ipynb | 812 |
1 files changed, 0 insertions, 812 deletions
diff --git a/Thermodynamics_An_Engineering_Approach/Chapter17.ipynb b/Thermodynamics_An_Engineering_Approach/Chapter17.ipynb deleted file mode 100755 index 5b1b7ade..00000000 --- a/Thermodynamics_An_Engineering_Approach/Chapter17.ipynb +++ /dev/null @@ -1,812 +0,0 @@ -{
- "metadata": {
- "name": ""
- },
- "nbformat": 3,
- "nbformat_minor": 0,
- "worksheets": [
- {
- "cells": [
- {
- "cell_type": "heading",
- "level": 1,
- "metadata": {},
- "source": [
- "Chapter 17: Compressible Flow"
- ]
- },
- {
- "cell_type": "heading",
- "level": 2,
- "metadata": {},
- "source": [
- "Example 17-1 ,Page No.826"
- ]
- },
- {
- "cell_type": "code",
- "collapsed": false,
- "input": [
- "#given data\n",
- "V1=250.0;#velocity of aircraft in m/s\n",
- "T1=255.07;#ambient air temperature in K\n",
- "P1=54.05;#atmospheric pressure in kPa\n",
- "h=5000.0;#altitude in m\n",
- "\n",
- "#from Table A-2a\n",
- "cp=1.005;#in kJ/kg-K\n",
- "k=1.4;\n",
- "\n",
- "#calculations\n",
- "T01=T1+V1**2/(2*cp*1000);#factor of 1000 to convert kJ to J\n",
- "P01=P1*(T01/T1)**(k/(k-1));\n",
- "#given pressure ratio in compressor *\n",
- "# T02 = T01*(P02/P01)^((k-1)/k)\n",
- "T02 = T01*(8)**((k-1)/k);\n",
- "win=cp*(T02-T01);\n",
- "print'the stagnation pressure at the compressor inlet %f kPa'%round(P01,2);\n",
- "print'the required compressor work per unit mass %f kJ/kg'%round(win,1)"
- ],
- "language": "python",
- "metadata": {},
- "outputs": [
- {
- "output_type": "stream",
- "stream": "stdout",
- "text": [
- "the stagnation pressure at the compressor inlet 80.840000 kPa\n",
- "the required compressor work per unit mass 233.400000 kJ/kg\n"
- ]
- }
- ],
- "prompt_number": 5
- },
- {
- "cell_type": "heading",
- "level": 2,
- "metadata": {},
- "source": [
- "Example 17-2 ,Page No.829"
- ]
- },
- {
- "cell_type": "code",
- "collapsed": false,
- "input": [
- "from math import sqrt\n",
- "\n",
- "#given data\n",
- "V=200.0;#air velocity in m/s\n",
- "T=30+273.0;#air temperature in K\n",
- "\n",
- "#from Table A-2a\n",
- "R=0.287;#in kJ/kg-K\n",
- "k=1.4;\n",
- "\n",
- "#calculations\n",
- "c=sqrt(k*R*T*1000);#factor of 1000 to convert kJ to J\n",
- "print'the speed of sound %i m/s'%round(c);\n",
- "Ma=V/c;\n",
- "print'the Mach number at the diffuser inlet is %f'%round(Ma,3)"
- ],
- "language": "python",
- "metadata": {},
- "outputs": [
- {
- "output_type": "stream",
- "stream": "stdout",
- "text": [
- "the speed of sound 349 m/s\n",
- "the Mach number at the diffuser inlet is 0.573000\n"
- ]
- }
- ],
- "prompt_number": 7
- },
- {
- "cell_type": "heading",
- "level": 2,
- "metadata": {},
- "source": [
- "Example 17-3 ,Page No.829"
- ]
- },
- {
- "cell_type": "code",
- "collapsed": false,
- "input": [
- "from math import sqrt\n",
- "\n",
- "#given data\n",
- "T0=200+273.0;#intial temperature in K\n",
- "P0=1400.0;#intial pressure in kPa\n",
- "#stagnant temp. & pressure is same as inlet due to small inlet velocity\n",
- "P=1200.0;#pressure corresponding to a pressure drop of 200 kPa\n",
- "m=3.0;#mass flow rate in kg/s\n",
- "\n",
- "#from Table A-2a\n",
- "cp=0.846;#in kJ/kg-K\n",
- "R=0.1889;#in kJ/kg-K\n",
- "k=1.289;\n",
- "\n",
- "#calculations\n",
- "T=T0*(P/P0)**((k-1)/k);\n",
- "V=sqrt(2*cp*(T0-T)*1000);#factor of 1000 to convert kJ to J\n",
- "p=P/(R*T);\n",
- "A=m/(p*V);\n",
- "c=sqrt(k*R*T*1000);#factor of 1000 to convert kJ to J\n",
- "Ma=V/c;\n",
- "print'velocity %f m/s'%round(V,1);\n",
- "print'density %f kg/m^3'%round(p,1);\n",
- "print'flow area %f cm^2'%round((A*10000),1);\n",
- "print'Mach number is %f'%round(Ma,3);"
- ],
- "language": "python",
- "metadata": {},
- "outputs": [
- {
- "output_type": "stream",
- "stream": "stdout",
- "text": [
- "velocity 164.900000 m/s\n",
- "density 13.900000 kg/m^3\n",
- "flow area 13.100000 cm^2\n",
- "Mach number is 0.494000\n"
- ]
- }
- ],
- "prompt_number": 10
- },
- {
- "cell_type": "heading",
- "level": 2,
- "metadata": {},
- "source": [
- "Example 17-4 ,Page No.836"
- ]
- },
- {
- "cell_type": "code",
- "collapsed": false,
- "input": [
- "#given data\n",
- "T0=200+273.0;#intial temperature in K\n",
- "P0=1400.0;#intial pressure in kPa\n",
- "\n",
- "#from Table A-2a\n",
- "k=1.289;\n",
- "\n",
- "#calculations\n",
- "#Tc & Tr stands for critical temp and ratio respectively\n",
- "#Pc & Pr stands for critical temp and ratio respectively\n",
- "Tr=2/(k+1);\n",
- "Pr=(2/(k+1))**(k/(k-1));\n",
- "Tc=Tr*T0;\n",
- "Pc=Pr*P0;\n",
- "print'critical temperature %i K'%round(Tc);\n",
- "print'critical pressure %i kPa'%round(Pc)\n"
- ],
- "language": "python",
- "metadata": {},
- "outputs": [
- {
- "output_type": "stream",
- "stream": "stdout",
- "text": [
- "critical temperature 413 K\n",
- "critical pressure 767 kPa\n"
- ]
- }
- ],
- "prompt_number": 12
- },
- {
- "cell_type": "heading",
- "level": 2,
- "metadata": {},
- "source": [
- "Example 17-5 ,Page No.839"
- ]
- },
- {
- "cell_type": "code",
- "collapsed": false,
- "input": [
- "from math import sqrt\n",
- "\n",
- "#given data\n",
- "Vi=150.0;#air velocity in m/s\n",
- "Ti=600+273.0;#air temperature in K\n",
- "Pi=1.0;#air pressure in MPa\n",
- "At=50.0/10000.0;#nozzle throat area in m^2\n",
- "\n",
- "#from Table A-2a\n",
- "R=0.287;#in kJ/kg-K\n",
- "cp=1.005;#in kJ/kg-K\n",
- "k=1.4;\n",
- "\n",
- "#calculations\n",
- "Toi=Ti+Vi**2/(2*cp*1000);#factor of 1000 to convert kJ to J\n",
- "Poi=Pi*(Toi/Ti)**(k/(k-1));\n",
- "#flow is isentropic \n",
- "#stagnation temp. and pressure values remain constant\n",
- "To=Toi;\n",
- "Po=Poi;\n",
- "#from Table 17\u20132\n",
- "#The critical-pressure ratio is 0.5283\n",
- "\n",
- "#Part a\n",
- "Pb=0.7;\n",
- "Pca=Pb/Po;\n",
- "# Pca > 0.5283\n",
- "#exit plane pressure is equal to the back pressure\n",
- "Pt=Pb;\n",
- "#from Table A\u201332\n",
- "Mat=0.778;\n",
- "#Tt/To = 0.892\n",
- "Tt=0.892*To;\n",
- "pt=Pt*1000/(R*Tt);#factor of 1000 to convert MPa to kPa\n",
- "Vt=Mat*sqrt(k*R*Tt*1000);#factor of 1000 to convert kJ to J\n",
- "ma=pt*At*Vt;\n",
- "print'the mass flow rate through the nozzle when the back pressure is 0.7 MPa %f kg/s'%round(ma,2);\n",
- "\n",
- "#Part b\n",
- "Pb=0.4;\n",
- "Pca=Pb/Po;\n",
- "# Pca < 0.5283\n",
- "#sonic conditions exists at the exit\n",
- "Ma=1;\n",
- "mb=At*(Po*1000)*(sqrt(k*1000/(R*To)))*(2/(k+1))**((k+1)/(2*(k-1)));#factor of 1000 to convert MPa to kPa and kJ to J\n",
- "print'the mass flow rate through the nozzle when the back pressure is 0.4 MPa %f kg/s'%round(mb,2);\n"
- ],
- "language": "python",
- "metadata": {},
- "outputs": [
- {
- "output_type": "stream",
- "stream": "stdout",
- "text": [
- "the mass flow rate through the nozzle when the back pressure is 0.7 MPa 6.770000 kg/s\n",
- "the mass flow rate through the nozzle when the back pressure is 0.4 MPa 7.110000 kg/s\n"
- ]
- }
- ],
- "prompt_number": 14
- },
- {
- "cell_type": "heading",
- "level": 2,
- "metadata": {},
- "source": [
- "Example 17-6 ,Page No.840"
- ]
- },
- {
- "cell_type": "code",
- "collapsed": false,
- "input": [
- "#given data\n",
- "T1=400;#intial temperature in K\n",
- "P1=100;#intial pressure in kPa\n",
- "Ma1=0.3;#intial mach no\n",
- "A21=0.8;#A2/A1 as flow area has been reduced by 20 percent\n",
- "\n",
- "#assumption\n",
- "k=1.4;\n",
- "\n",
- "#from Table A\u201332\n",
- "#at Ma1=0.3\n",
- "#s stands for * symbol\n",
- "A1s = 2.0351;#A1/As\n",
- "T10 = 0.9823;#T1/T0\n",
- "P10 = 0.9305;#P1/P0\n",
- "A2s = A21*A1s;#A2/As\n",
- "#at this value of A2/As\n",
- "T20=0.9701;#T2/T0\n",
- "P20=0.8993;#P2/P0\n",
- "Ma2=0.391;\n",
- "\n",
- "#calculations\n",
- "T2=T1*T20/T10;\n",
- "P2=P1*P20/P10;\n",
- "print'Ma2 is %f'%round(Ma2,3);\n",
- "print'T2 %i K is'%round(T2);\n",
- "print'P2 %f kPa is'%round(P2,1)"
- ],
- "language": "python",
- "metadata": {},
- "outputs": [
- {
- "output_type": "stream",
- "stream": "stdout",
- "text": [
- "Ma2 is 0.391000\n",
- "T2 395 K is\n",
- "P2 96.600000 kPa is\n"
- ]
- }
- ],
- "prompt_number": 16
- },
- {
- "cell_type": "heading",
- "level": 2,
- "metadata": {},
- "source": [
- "Example 17-7 ,Page No.844"
- ]
- },
- {
- "cell_type": "code",
- "collapsed": false,
- "input": [
- "#given data \n",
- "T0=800;#intial temperature in K\n",
- "P0=1;#intial pressure in MPa\n",
- "Vi=0;#negligible intial velcity\n",
- "At=20;#throat area in cm^2\n",
- "Mae=2;#exit Mach number\n",
- "\n",
- "#from Table A-2a\n",
- "R=0.287;#in kJ/kg-K\n",
- "k=1.4;\n",
- "\n",
- "#calculations\n",
- "\n",
- "#part - a\n",
- "# Mach no. at exit is 2 hence sonic conditions at throat\n",
- "p0=P0*1000/(R*T0);#factor of 1000 to convert MPa to kPa\n",
- "#from Table A-32 at Mat=1\n",
- "#s stands for * symbol\n",
- "Ps0 = 0.5283;#Ts/T0\n",
- "Ts0 = 0.8333;#Ps/P0\n",
- "ps0=0.6339;#ps/p0\n",
- "Ps=Ps0*P0;\n",
- "Ts=Ts0*T0;\n",
- "ps=ps0*p0;\n",
- "As=At;\n",
- "Vs=sqrt(k*R*Ts*1000);#factor of 1000 to convert kJ to J\n",
- "print('the throat conditions');\n",
- "print'Presssure %f MPa'%round(Ps,4);\n",
- "print'Temperature %f K'%round(Ts,1);\n",
- "print'density %f kg/m^3'%round(ps,3);\n",
- "print'area %f cm^2'%round(As);\n",
- "print'velocity %f m/s'%round(Vs,1);\n",
- "\n",
- "#part - b\n",
- "#from Table A-32\n",
- "#at Mae=2\n",
- "Te0 = 0.5556;#Te/T0\n",
- "Pe0 = 0.1278;#Pe/P0\n",
- "pe0= 0.2300;#pe/p0\n",
- "Ae0= 1.6875;#Ae/Ao\n",
- "Pe=Pe0*P0;\n",
- "Te=Te0*T0;\n",
- "pe=pe0*p0;\n",
- "Ae=Ae0*At;\n",
- "Ve=Mae*sqrt(k*R*Te*1000);#factor of 1000 to convert kJ to J\n",
- "print('the exit plane conditions, including the exit area');\n",
- "print'Presssure %f MPa'%round(Pe,4);\n",
- "print'Temperature %f K'%round(Te,1);\n",
- "print'density %f kg/m^3'%round(pe,3);\n",
- "print'area %f cm^2'%round(Ae,2);\n",
- "print'velocity %f m/s'%round(Ve,1);\n",
- "#part - c\n",
- "m=ps*As*Vs/10000;#factor of 10000 to convert cm^2 to m^2\n",
- "print'the mass flow rate through the nozzle %f kg/s'%round(m,2);\n",
- "\n"
- ],
- "language": "python",
- "metadata": {},
- "outputs": [
- {
- "output_type": "stream",
- "stream": "stdout",
- "text": [
- "the throat conditions\n",
- "Presssure 0.528300 MPa\n",
- "Temperature 666.600000 K\n",
- "density 2.761000 kg/m^3\n",
- "area 20.000000 cm^2\n",
- "velocity 517.500000 m/s\n",
- "the exit plane conditions, including the exit area\n",
- "Presssure 0.127800 MPa\n",
- "Temperature 444.500000 K\n",
- "density 1.002000 kg/m^3\n",
- "area 33.750000 cm^2\n",
- "velocity 845.200000 m/s\n",
- "the mass flow rate through the nozzle 2.860000 kg/s\n"
- ]
- }
- ],
- "prompt_number": 20
- },
- {
- "cell_type": "heading",
- "level": 2,
- "metadata": {},
- "source": [
- "Example 17-9 ,Page No.850"
- ]
- },
- {
- "cell_type": "code",
- "collapsed": false,
- "input": [
- "from math import log,sqrt\n",
- "\n",
- "#data from Ex - 17.7\n",
- "m=2.86;\n",
- "Ma1=2;\n",
- "P01=1;\n",
- "P1=0.1278;\n",
- "T1=444.5;\n",
- "p1=1.002;\n",
- "\n",
- "#from Table A-2a\n",
- "R=0.287;#in kJ/kg-K\n",
- "cp=1.005;#in kJ/kg-K\n",
- "k=1.4;\n",
- "\n",
- "#calculations\n",
- "\n",
- "#part - a\n",
- "#from Table A-33 at Ma1=2.0\n",
- "Ma2=0.5774;\n",
- "P0201=0.7209;#P02/P01\n",
- "P21=4.5;#P2/P1;\n",
- "T21=1.6875;#T2/T1\n",
- "p21=2.6667;#p2/p1\n",
- "P02=P0201*P01;\n",
- "P2=P21*P1;\n",
- "T2=T21*T1;\n",
- "p2=p21*p1;\n",
- "print'the stagnation pressure %f MPa'%round(P02,3);\n",
- "print'the static pressure %f MPa'%round(P2,3);\n",
- "print'static temperature %f K'%round(T2);\n",
- "print'static density %f kg/m^3'%round(p2,2);\n",
- "\n",
- "#part - b\n",
- "#s21 = s2 - s1\n",
- "s21=cp*log(T2/T1)-R*log(P2/P1);\n",
- "print'the entropy change across the shock %fkJ/kg-K'%round(s21,4);\n",
- "\n",
- "#part - c\n",
- "V2=Ma2*sqrt(k*R*T2*1000);#factor of 1000 to convert kJ to J\n",
- "print'the exit velocity %f m/s'%round(V2);\n",
- "\n",
- "#part - d\n",
- "print('flow rate is not affected by presence of shock waves amd remains 2.86 kg/sec')"
- ],
- "language": "python",
- "metadata": {},
- "outputs": [
- {
- "output_type": "stream",
- "stream": "stdout",
- "text": [
- "the stagnation pressure 0.721000 MPa\n",
- "the static pressure 0.575000 MPa\n",
- "static temperature 750.000000 K\n",
- "static density 2.670000 kg/m^3\n",
- "the entropy change across the shock 0.094200kJ/kg-K\n",
- "the exit velocity 317.000000 m/s\n",
- "flow rate is not affected by presence of shock waves amd remains 2.86 kg/sec\n"
- ]
- }
- ],
- "prompt_number": 22
- },
- {
- "cell_type": "heading",
- "level": 2,
- "metadata": {},
- "source": [
- "Example 17-10 ,Page No.858"
- ]
- },
- {
- "cell_type": "code",
- "collapsed": false,
- "input": [
- "from math import sin,pi\n",
- "\n",
- "#given data\n",
- "#using protactor frpm Fig 17-36\n",
- "u=19;#u stands for angle of the mach lines\n",
- "\n",
- "#calculations\n",
- "#by Eq. 17-47\n",
- "#i.e u= asin(1/Ma)\n",
- "Ma=1/sin(u*pi/180);#converting to radians\n",
- "print'The Mach number is %f'%round(Ma,2)\n"
- ],
- "language": "python",
- "metadata": {},
- "outputs": [
- {
- "output_type": "stream",
- "stream": "stdout",
- "text": [
- "The Mach number is 3.070000\n"
- ]
- }
- ],
- "prompt_number": 27
- },
- {
- "cell_type": "heading",
- "level": 2,
- "metadata": {},
- "source": [
- "Example 17-11 ,Page No.858"
- ]
- },
- {
- "cell_type": "code",
- "collapsed": false,
- "input": [
- "from math import sin,pi\n",
- "\n",
- "#given data\n",
- "Ma1=2;#Supersonic air mach no\n",
- "P1=75;#Supersonic air at pressure in kPa\n",
- "O=10*pi/180;#converting to radians & angle b/w shock wave and normal\n",
- "\n",
- "#constants used\n",
- "k=1.4;\n",
- "\n",
- "#calcualtions\n",
- "#with given values of Ma1 and O from Eq 17-46\n",
- "Bweak=39.3*pi/180;#converting to radians\n",
- "Bstrong=83.7*pi/180;#converting to radians\n",
- "#Weak shock\n",
- "Ma1w=Ma1*sin(Bweak);\n",
- "#Strong shock\n",
- "Ma1s=Ma1*sin(Bstrong);\n",
- "#from second part Eq 17-40\n",
- "Ma2w=0.8032;\n",
- "Ma2s=0.5794;\n",
- "#pressure ratio = (2*k*Ma^2 - k + 1)/(k + 1 )\n",
- "#Weak shock\n",
- "P2w=P1*(2*k*Ma1w**2 - k + 1)/(k + 1 );\n",
- "print'pressure for weak shock %i kPa'%round(P2w);\n",
- "#Strong shock\n",
- "P2s=P1*(2*k*Ma1s**2 - k + 1)/(k + 1 );\n",
- "print'pressure for strong shock %i kPa'%round(P2s);\n",
- "#Weak shock\n",
- "Ma2=Ma2w/sin(Bweak-O);\n",
- "print'Mach number downstream for weak shock is %f'%round(Ma2,2);\n",
- "#Strong shock\n",
- "Ma2=Ma2s/sin(Bstrong-O);\n",
- "print'Mach number downstream for strong shock is %f'%round(Ma2,3);"
- ],
- "language": "python",
- "metadata": {},
- "outputs": [
- {
- "output_type": "stream",
- "stream": "stdout",
- "text": [
- "pressure for weak shock 128 kPa\n",
- "pressure for strong shock 333 kPa\n",
- "Mach number downstream for weak shock is 1.640000\n",
- "Mach number downstream for strong shock is 0.604000\n"
- ]
- }
- ],
- "prompt_number": 35
- },
- {
- "cell_type": "heading",
- "level": 1,
- "metadata": {},
- "source": [
- "Example 17-12 ,Page No.859"
- ]
- },
- {
- "cell_type": "code",
- "collapsed": false,
- "input": [
- "from math import sqrt,pi,atan\n",
- "\n",
- "#given data\n",
- "Ma1=2;#Supersonic air mach no\n",
- "P1=230;#Supersonic air pressure in kPa\n",
- "O=10*pi/180;#converting to radians & O stands for angle of the mach lines\n",
- "\n",
- "#constants used\n",
- "k=1.4;\n",
- "\n",
- "#calculations\n",
- "#Eq. 17\u201349 for the upstream Prandtl\u2013Meyer function\n",
- "vMa1=sqrt((k+1)/(k-1))*atan(sqrt((k-1)*(Ma1**2-1)/(k+1))*pi/180)-atan(sqrt(Ma1**2-1)*pi/180);#converting to radians\n",
- "#Eq. 17\u201348 to calculate the downstream Prandtl\u2013Meyer function\n",
- "vMa2=O+vMa1;\n",
- "#using equation solver as implict nature of Eq 17-49\n",
- "Ma2=2.385;\n",
- "print'downstream Mach number Ma2 is %f'%round(Ma2,3);\n",
- "#P2 = (P2/P0)/(P1/P0) * P1\n",
- "P2= (1 + (k-1)*Ma2**2/2 )**(-k/(k-1)) / (1 + (k-1)*Ma1**2/2 )**(-k/(k-1)) * P1;\n",
- "print'downstream pressure %i kPa'%round(P2)\n"
- ],
- "language": "python",
- "metadata": {},
- "outputs": [
- {
- "output_type": "stream",
- "stream": "stdout",
- "text": [
- "downstream Mach number Ma2 is 2.385000\n",
- "downstream pressure 126 kPa\n"
- ]
- }
- ],
- "prompt_number": 37
- },
- {
- "cell_type": "heading",
- "level": 2,
- "metadata": {},
- "source": [
- "Example 17-15 ,Page No.868"
- ]
- },
- {
- "cell_type": "code",
- "collapsed": false,
- "input": [
- "from math import pi,sqrt\n",
- "\n",
- "#given data\n",
- "P1=480.0;#intial pressure in kPa\n",
- "T1=550.0;#intial temperature in K\n",
- "V1=80.0;#intial velocity in m/s\n",
- "d1=15.0/100.0;#diameter in m\n",
- "AF=40.0;#air to fuel ratio\n",
- "HV=40000.0;#heating value in kJ/kg\n",
- "\n",
- "#from Table A-2a\n",
- "R=0.287;#in kJ/kg-K\n",
- "cp=1.005;#in kJ/kg-K\n",
- "k=1.4;\n",
- "\n",
- "#calculations\n",
- "p1=P1/(R*T1);\n",
- "A1=pi*d1**2/4;\n",
- "mair=p1*A1*V1;\n",
- "mfuel=mair/AF;\n",
- "Q=mfuel*HV;\n",
- "q=Q/mair;\n",
- "T01=T1+V1**2/(2*cp);\n",
- "c1=sqrt(k*R*T1*1000);#factor of 1000 to convert kJ to J\n",
- "Ma1=V1/c1;\n",
- "#exit stagnation energy equation q= Cp (T02 - T01)\n",
- "T02=T01+q/cp;\n",
- "#from Table A\u201334\n",
- "#at Ma1\n",
- "#s stands for * symbol\n",
- "T0s=0.1291;#T0/Ts\n",
- "Ts0=T01/T0s;\n",
- "T2s=T02/Ts0;#T02/T*0\n",
- "#from Table A\u201334 at this ratio\n",
- "Ma2=0.3142;\n",
- "#Rayleigh flow relations corresponding to the inlet and exit Mach no\n",
- "#at Ma1\n",
- "T1s=0.1541;#T1/Ts\n",
- "P1s=2.3065;#P1/Ps\n",
- "V1s=0.0668;#V1/Vs\n",
- "#at Ma2\n",
- "T2s=0.4389;#T2/Ts\n",
- "P2s=2.1086;#P2/Ps\n",
- "V2s=0.2082;#V2/Vs\n",
- "T2=T2s/T1s*T1;\n",
- "P2=P2s/P1s*P1;\n",
- "V2=V2s/V1s*V1; \n",
- "print'Mach Number at exit is %f'%round(Ma2,4);\n",
- "print'Presssure %i MPa'%round(P2);\n",
- "print'Temperature %i K'%round(T2);\n",
- "print'velocity %i m/s'%round(V2);"
- ],
- "language": "python",
- "metadata": {},
- "outputs": [
- {
- "output_type": "stream",
- "stream": "stdout",
- "text": [
- "Mach Number at exit is 0.314200\n",
- "Presssure 439 MPa\n",
- "Temperature 1566 K\n",
- "velocity 249 m/s\n"
- ]
- }
- ],
- "prompt_number": 41
- },
- {
- "cell_type": "heading",
- "level": 2,
- "metadata": {},
- "source": [
- "Example 17-16 ,Page No.870"
- ]
- },
- {
- "cell_type": "code",
- "collapsed": false,
- "input": [
- "from math import sqrt\n",
- "\n",
- "#given data\n",
- "P01=2000;#entry pressure in kPa\n",
- "T1=400;#entry temperature in C\n",
- "V1=0;#negligible velocity at entry\n",
- "nN=0.93;#overall nozzle efficiency\n",
- "m=2.5;#mass flow rate in kg/s\n",
- "P2=300;#exit pressure in kPa\n",
- "\n",
- "#calculations\n",
- "\n",
- "#part - a\n",
- "P201=P2/P01;\n",
- "#critical pressure ratio at this values is 0.546\n",
- "Pt=0.546*P01;\n",
- "#at inlet\n",
- "h1=3248.4;\n",
- "h01=h1;\n",
- "s1=7.1292;\n",
- "#at throat\n",
- "st=s1;\n",
- "ht=3076.8;\n",
- "vt=0.24196;\n",
- "Vt=sqrt(2*(h01-ht)*1000);#factor of 1000 to convert kJ to J\n",
- "At=m*vt/Vt;\n",
- "#at state 2s\n",
- "s2s=s1;\n",
- "h2s=2783.6;\n",
- "#nN = (h01 - h2)/ (h01 - h2s)\n",
- "h2=h01-nN*(h01-h2s);\n",
- "#at P2 and h2\n",
- "v2=0.67723;\n",
- "s2=7.2019;\n",
- "V2=sqrt(2*(h01-h2)*1000);#factor of 1000 to convert kJ to J\n",
- "A2=m*v2/V2;\n",
- "print'throat area %f cm^2'%round((At*10000),2);\n",
- "print'exit area %f cm^2'%round((A2*10000),2);\n",
- "\n",
- "#part - b\n",
- "# at st=7.1292\n",
- "#pressures of 1.115 and 1.065 MPa\n",
- "#c calculated using tables\n",
- "c=sqrt((1115-1065)/(1/0.23776 - 1/0.24633)*1000);#factor of 1000 to convert kPa to Pa\n",
- "Ma=Vt/c;\n",
- "print'the Mach number at the throat is %f'%round(Ma,2);\n",
- "# at s2=7.2019\n",
- "#pressures of 325 and 275 kPa\n",
- "c=sqrt((325-276)/(1/0.63596 - 1/0.72245)*1000);#factor of 1000 to convert kPa to Pa\n",
- "Ma=V2/c;\n",
- "print'the Mach number at the nozzle exit is %f'%round(Ma,2)"
- ],
- "language": "python",
- "metadata": {},
- "outputs": [
- {
- "output_type": "stream",
- "stream": "stdout",
- "text": [
- "throat area 10.330000 cm^2\n",
- "exit area 18.210000 cm^2\n",
- "the Mach number at the throat is 1.000000\n",
- "the Mach number at the nozzle exit is 1.820000\n"
- ]
- }
- ],
- "prompt_number": 44
- }
- ],
- "metadata": {}
- }
- ]
-}
\ No newline at end of file |