From 92cca121f959c6616e3da431c1e2d23c4fa5e886 Mon Sep 17 00:00:00 2001 From: hardythe1 Date: Tue, 7 Apr 2015 15:58:05 +0530 Subject: added books --- Fundamentals_Of_Thermodynamics/Chapter17.ipynb | 434 +++++++++++++++++++++++++ 1 file changed, 434 insertions(+) create mode 100755 Fundamentals_Of_Thermodynamics/Chapter17.ipynb (limited to 'Fundamentals_Of_Thermodynamics/Chapter17.ipynb') 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 -- cgit