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Diffstat (limited to 'Fundamentals_Of_Thermodynamics/Chapter17.ipynb')
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diff --git a/Fundamentals_Of_Thermodynamics/Chapter17.ipynb b/Fundamentals_Of_Thermodynamics/Chapter17.ipynb new file mode 100755 index 00000000..4ae8005b --- /dev/null +++ b/Fundamentals_Of_Thermodynamics/Chapter17.ipynb @@ -0,0 +1,434 @@ +{
+ "metadata": {
+ "name": "",
+ "signature": "sha256:70b7f86a423a7c9685f997491946441e1c53cfe8fe328afd6e5b37a44e4dce11"
+ },
+ "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": [
+ "Ex17.1:PG-710"
+ ]
+ },
+ {
+ "cell_type": "code",
+ "collapsed": false,
+ "input": [
+ "#ques1\n",
+ "#to determine isentropic stagnation pressure and temperature \n",
+ "\n",
+ "T=300;#Temperature of air in K\n",
+ "P=150;#Pressure of air in kPa\n",
+ "v=200;#velocity of air flow n m/s\n",
+ "Cp=1.004;#specific heat at constant pressure in kJ/kg\n",
+ "To=v**2/(2000*Cp)+T;#stagnation temperature in K\n",
+ "k=1.4;#constant\n",
+ "Po=P*(To/T)**(k/(k-1));#stagnation pressure in kPa\n",
+ "print 'Stagnation Temperature is ',round(To,1),' K \\n'\n",
+ "print 'Stagnation Pressure is ',round(Po,2),'kPa \\n'"
+ ],
+ "language": "python",
+ "metadata": {},
+ "outputs": [
+ {
+ "output_type": "stream",
+ "stream": "stdout",
+ "text": [
+ "Stagnation Temperature is 319.9 K \n",
+ "\n",
+ "Stagnation Pressure is 187.85 kPa \n",
+ "\n"
+ ]
+ }
+ ],
+ "prompt_number": 5
+ },
+ {
+ "cell_type": "heading",
+ "level": 2,
+ "metadata": {},
+ "source": [
+ "Ex17.2:PG-713"
+ ]
+ },
+ {
+ "cell_type": "code",
+ "collapsed": false,
+ "input": [
+ "#ques2\n",
+ "#to determine the force\n",
+ "\n",
+ "#initializing variables\n",
+ "mdot=-1 # mass flow rate out of control volume in kg/s\n",
+ "Vx=-1 # x component of velocity of control volume in m/s\n",
+ "Vy=10 # y component of velocity of control volume in m/s\n",
+ "\n",
+ "Fx=mdot*Vx # Force in X direction\n",
+ "\n",
+ "Fy=mdot*Vy # Force in Y direction\n",
+ "\n",
+ "print \"the force the man exert on the wheelbarrow\",round(Fx),\"N\"\n",
+ "print \"the force the floor exerts on the wheelbarrow\",round(Fy),\"N\"\n",
+ "\n",
+ "\n"
+ ],
+ "language": "python",
+ "metadata": {},
+ "outputs": [
+ {
+ "output_type": "stream",
+ "stream": "stdout",
+ "text": [
+ "the force the man exert on the wheelbarrow 1.0 N\n",
+ "the force the floor exerts on the wheelbarrow -10.0 N\n"
+ ]
+ }
+ ],
+ "prompt_number": 6
+ },
+ {
+ "cell_type": "heading",
+ "level": 2,
+ "metadata": {},
+ "source": [
+ "Ex17.3:PG-715"
+ ]
+ },
+ {
+ "cell_type": "code",
+ "collapsed": false,
+ "input": [
+ "#ques3\n",
+ "#determining the thrust acting on a control surface\n",
+ "\n",
+ "#i-inlet\n",
+ "#e-exit\n",
+ "#using momentum equation on control surface in x direction\n",
+ "me=20.4;#mass exiting in kg\n",
+ "mi=20;#mass entering in kg\n",
+ "ve=450;#exit velocity in m/s\n",
+ "vi=100;#inlet velocity in m/s\n",
+ "Pi=95;#Pressure at inlet in kPa\n",
+ "Pe=125;#Pressure at exit in kPa\n",
+ "Po=100;#surrounding pressure in kPa\n",
+ "Ai=0.2;#inlet area in m^2\n",
+ "Ae=0.1;#exit area in m^2\n",
+ "Rx=(me*ve-mi*vi)/1000-(Pi-Po)*Ai+(Pe-Po)*Ae;#thrust in x direction in kN\n",
+ "\n",
+ "print \"Thrust acting in x direction is \",round(Rx,2),\"kN\""
+ ],
+ "language": "python",
+ "metadata": {},
+ "outputs": [
+ {
+ "output_type": "stream",
+ "stream": "stdout",
+ "text": [
+ "Thrust acting in x direction is 10.68 kN\n"
+ ]
+ }
+ ],
+ "prompt_number": 11
+ },
+ {
+ "cell_type": "heading",
+ "level": 2,
+ "metadata": {},
+ "source": [
+ "Ex17.4:PG-717"
+ ]
+ },
+ {
+ "cell_type": "code",
+ "collapsed": false,
+ "input": [
+ "#ques4\n",
+ "#to determine increase in enthalpy\n",
+ "#initializing variables\n",
+ "#i-inlet\n",
+ "#e-exit\n",
+ "\n",
+ "T=25+273 # temperature in kelvin\n",
+ "v=0.001003 # specific volume of water in kg/m^3 at 25 *c from table B.1.1 \n",
+ "ve=7;#exit velocity in m/s\n",
+ "vi=30;#inlet velocity in m/s\n",
+ "Pi=350;#Pressure at inlet in kPa\n",
+ "Pe=600;#Pressure at exit in kPa\n",
+ "\n",
+ "#using momentum equation on control surface \n",
+ "Pes= (vi**2-ve**2)/(2*v*1000)+Pi # exit pressure for reversible diffuser\n",
+ "delH=(vi**2-ve**2)/(2*1000.0) # change in enthalpy from first law in kJ/kg\n",
+ "delU=delH-v*(Pe-Pi) # change in internal energy in kJ/kg\n",
+ "delS=delU/T # change in entropy in kJ/kg.K\n",
+ "print\"the exit pressure for reversible diffuser is \",round(Pes),\"kPa\"\n",
+ "print\"the increase in enthalpy is \",round(delH,5),\"kJ/kg\"\n",
+ "print\"the increase in internal energy is \",round(delU,5),\"kJ/kg\"\n",
+ "print\"the increase in entropy is \",round(delS,6),\"kJ/kg.K\"\n",
+ "\n",
+ "\n",
+ "\n",
+ "\n",
+ "\n",
+ "\n",
+ "\n"
+ ],
+ "language": "python",
+ "metadata": {},
+ "outputs": [
+ {
+ "output_type": "stream",
+ "stream": "stdout",
+ "text": [
+ "the exit pressure for reversible diffuser is 774.0 kPa\n",
+ "the increase in enthalpy is 0.4255 kJ/kg\n",
+ "the increase in internal energy is 0.17475 kJ/kg\n",
+ "the increase in entropy is 0.000586 kJ/kg.K\n"
+ ]
+ }
+ ],
+ "prompt_number": 19
+ },
+ {
+ "cell_type": "heading",
+ "level": 2,
+ "metadata": {},
+ "source": [
+ "Ex17.5:PG-720"
+ ]
+ },
+ {
+ "cell_type": "code",
+ "collapsed": false,
+ "input": [
+ "#ques5\n",
+ "#determining velocity of sound in air\n",
+ "import math\n",
+ "k=1.4;#constant\n",
+ "R=0.287;#gas constant\n",
+ "#at 300K\n",
+ "T1=300;# temperature in kelvin\n",
+ "c1=math.sqrt(k*R*T1*1000)\n",
+ "print \"Speed of sound at 300 K is\",round(c1,1),\" m/s\" \n",
+ "#at 1000K\n",
+ "T2=1000;# temperature in kelvin\n",
+ "c2=math.sqrt(k*R*T2*1000)\n",
+ "print \"Speed of sound at 1000 K is\",round(c2,1),\" m/s\""
+ ],
+ "language": "python",
+ "metadata": {},
+ "outputs": [
+ {
+ "output_type": "stream",
+ "stream": "stdout",
+ "text": [
+ "Speed of sound at 300 K is 347.2 m/s\n",
+ "Speed of sound at 1000 K is 633.9 m/s\n"
+ ]
+ }
+ ],
+ "prompt_number": 24
+ },
+ {
+ "cell_type": "heading",
+ "level": 2,
+ "metadata": {},
+ "source": [
+ "Ex17.6:PG-727"
+ ]
+ },
+ {
+ "cell_type": "code",
+ "collapsed": false,
+ "input": [
+ "#ques6\n",
+ "#determining mass flow rate through control volume\n",
+ "import math\n",
+ "k=1.4;#constant\n",
+ "R=0.287;#gas constant\n",
+ "To=360;#stagnation Temperature in K \n",
+ "T=To*0.8333;#Temperature of air in K, 0.8333 stagnation ratio from table\n",
+ "v=math.sqrt(k*R*T*1000);#velocity in m/s\n",
+ "P=528;#stagnation pressure in kPa\n",
+ "d=P/(R*T);#stagnation density in kg/m^3\n",
+ "A=500*10**-6;#area in m^2\n",
+ "ms=d*A*v;#mass flow rate in kg/s\n",
+ "print\" Mass flow rate at the throat section is\",round(ms,4),\"kg/s\"\n",
+ "#e-exit state\n",
+ "Te=To*0.9381;#exit temperature in K, ratio from table\n",
+ "ce=math.sqrt(k*R*Te*1000);#exit velocity of sound in m/s\n",
+ "Me=0.573;#Mach number\n",
+ "ve=Me*ce;\n",
+ "Pe=800;#exit pressure in kPa\n",
+ "de=Pe/R/Te;\n",
+ "mse=de*A*ve;\n",
+ "print\" Mass flow rate at the exit section is\",round(mse,4),\" kg/s\""
+ ],
+ "language": "python",
+ "metadata": {},
+ "outputs": [
+ {
+ "output_type": "stream",
+ "stream": "stdout",
+ "text": [
+ " Mass flow rate at the throat section is 1.0646 kg/s\n",
+ " Mass flow rate at the exit section is 0.8711 kg/s\n"
+ ]
+ }
+ ],
+ "prompt_number": 30
+ },
+ {
+ "cell_type": "heading",
+ "level": 2,
+ "metadata": {},
+ "source": [
+ "Ex17.7:PG-728"
+ ]
+ },
+ {
+ "cell_type": "code",
+ "collapsed": false,
+ "input": [
+ "#ques7\n",
+ "#determining exit properties in a control volume\n",
+ "import math\n",
+ "Po=1000;#stagnation pressure in kPa\n",
+ "To=360;#stagnation temperature in K\n",
+ "\n",
+ "#when diverging section acting as nozzle\n",
+ "\n",
+ "Pe1=0.0939*Po;#exit pressure of air in kPa\n",
+ "Te1=0.5089*To;#exit temperature in K\n",
+ "k=1.4;#constant\n",
+ "R=0.287;#gas constant for air\n",
+ "ce=math.sqrt(k*R*Te1*1000);#velocity of sound in exit section in m/s\n",
+ "Me=2.197;#mach number from table\n",
+ "ve1=Me*ce;#velocity of air at exit section in m/s\n",
+ "print \"When diverging section act as a nozzle :-\"\n",
+ "print \"Exit pressure is\",round(Pe1,4),\" kPa\"\n",
+ "print \"Exit Temperature\",round(Te1,1),\" K\"\n",
+ "print \"Exit velocity is\",round(ve1,1),\" m/s \"\n",
+ "\n",
+ "#when diverging section act as diffuser\n",
+ "\n",
+ "Me=0.308;\n",
+ "Pe2=0.0936*Po;#exit pressure of air in kPa\n",
+ "Te2=0.9812*To;#exit temperature in K\n",
+ "ce=math.sqrt(k*R*Te2*1000);#velocity of sound in exit section in m/s\n",
+ "ve2=Me*ce;\n",
+ "print \"When diverging section act as a diffuser :-\"\n",
+ "print \"Exit pressure is\",round(Pe2,1),\" kPa\"\n",
+ "print \"Exit Temperature\",round(Te2,2),\" K\"\n",
+ "print \"Exit velocity is\",round(ve2,),\" m/s \"\n",
+ "\n",
+ "# The value of Exit pressure when diverging section acts as diffuser is wrong\n",
+ "\n"
+ ],
+ "language": "python",
+ "metadata": {},
+ "outputs": [
+ {
+ "output_type": "stream",
+ "stream": "stdout",
+ "text": [
+ "When diverging section act as a nozzle :-\n",
+ "Exit pressure is 93.9 kPa\n",
+ "Exit Temperature 183.2 K\n",
+ "Exit velocity is 596.1 m/s \n",
+ "When diverging section act as a diffuser :-\n",
+ "Exit pressure is 93.6 kPa\n",
+ "Exit Temperature 353.23 K\n",
+ "Exit velocity is 116.0 m/s \n"
+ ]
+ }
+ ],
+ "prompt_number": 39
+ },
+ {
+ "cell_type": "heading",
+ "level": 2,
+ "metadata": {},
+ "source": [
+ "Ex17.9:PG-733"
+ ]
+ },
+ {
+ "cell_type": "code",
+ "collapsed": false,
+ "input": [
+ "#ques9\n",
+ "#determining exit plane properties in control volume\n",
+ "\n",
+ "#x-inlet\n",
+ "#y-exit\n",
+ "Mx=1.5;#mach number for inlet\n",
+ "My=0.7011;#mach number for exit\n",
+ "Px=272.4;#inlet pressure in kPa\n",
+ "Tx=248.3;#inlet temperature in K\n",
+ "Tox=360 # stagnation temperature in Kelvin\n",
+ "Pox=1000.0;#stagnation pressure for inlet\n",
+ "Py=2.4583*Px;# Pressure at 1.5 mach in kPa\n",
+ "Ty=1.320*Tx;# temperature at 1.5 mach in K\n",
+ "Poy=0.9298*Pox;# pressure at 1.5 mach in kPa\n",
+ "\n",
+ "Toy=Tox # constant\n",
+ "Me=0.339 # from table with A/A*=1.860 and M < 1\n",
+ "Pe=0.9222*Py;#Exit Pressure in kPa\n",
+ "Te=0.9771*Toy;#Exit temperature in K\n",
+ "Poe=0.9222*Poy;#Exit pressure in kPa\n",
+ "\n",
+ "print \"Exit Mach no.=\",Me\n",
+ "print \"Exit temperature =\",round(Te,2),\"K \"\n",
+ "print \"Exit pressure =\",round(Poe,1),\"kPa\""
+ ],
+ "language": "python",
+ "metadata": {},
+ "outputs": [
+ {
+ "output_type": "stream",
+ "stream": "stdout",
+ "text": [
+ "Exit Mach no.= 0.339\n",
+ "Exit temperature = 351.76 K \n",
+ "Exit pressure = 857.5 kPa\n"
+ ]
+ }
+ ],
+ "prompt_number": 50
+ },
+ {
+ "cell_type": "code",
+ "collapsed": false,
+ "input": [],
+ "language": "python",
+ "metadata": {},
+ "outputs": [],
+ "prompt_number": 45
+ },
+ {
+ "cell_type": "code",
+ "collapsed": false,
+ "input": [],
+ "language": "python",
+ "metadata": {},
+ "outputs": []
+ }
+ ],
+ "metadata": {}
+ }
+ ]
+}
\ No newline at end of file |