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diff --git a/Thermodynamics_by_F_P_Durham/chapter11.ipynb b/Thermodynamics_by_F_P_Durham/chapter11.ipynb new file mode 100755 index 00000000..ddbbdc4c --- /dev/null +++ b/Thermodynamics_by_F_P_Durham/chapter11.ipynb @@ -0,0 +1,484 @@ +{ + "metadata": { + "name": "", + "signature": "sha256:1bc460ef0aed5b06b0770ef04462064cc24e898eb90d5d0126bc2216d06cd7e0" + }, + "nbformat": 3, + "nbformat_minor": 0, + "worksheets": [ + { + "cells": [ + { + "cell_type": "heading", + "level": 1, + "metadata": {}, + "source": [ + "Chapter 11: Nozzels & Jet Propulsion" + ] + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Example 11.1, page no. 207" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "\n", + "import math\n", + "\n", + "\n", + "#initialization\n", + "P1 = 100.0 #lb/in^2\n", + "P2 = 14.7 #lb/in^2\n", + "T1 = 600+460.0 #R\n", + "T2 = 300+460.0 #R\n", + "area = 1.0 #in^2\n", + "\n", + "#calculation\n", + "#From steam tables\n", + "ht1 = 1329.1 \n", + "h2 = 1192.8\n", + "v2 = 30.53\n", + "Vel = math.sqrt(2*32.2*778.0*(ht1-h2))\n", + "\n", + "wdot = area*Vel/(144*v2)\n", + "\n", + "\n", + "#result\n", + "print \"Exit velocity = %d ft/sec\" %Vel\n", + "print \"Mass flow rate = %.3f lbm/sec\" %wdot\n", + "#difference in exit velocity due to rounding off in Python" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "Exit velocity = 2613 ft/sec\n", + "Mass flow rate = 0.594 lbm/sec\n" + ] + } + ], + "prompt_number": 7 + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Example 11.2, page no. 210" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "\n", + "import math\n", + "\n", + "#initialization\n", + "Pt1 = 100.0 #lb/in^2\n", + "P2 = 15.0 #lb/in^2\n", + "A = 1.0 #in^2\n", + "T = 500+460.0 #F\n", + "gamma = 1.4\n", + "\n", + "#calculation\n", + "Pratio = P2/Pt1\n", + "r1 = (P2/Pt1)**((gamma-1)/gamma)\n", + "r2 = (P2/Pt1)**(2/gamma)\n", + "r3 = (P2/Pt1)**((gamma+1)/gamma)\n", + "V2 = math.sqrt(2*gamma*32.2*53.3*T*(1-r1)/(gamma-1))\n", + "wdot = A*Pt1*math.sqrt(2*gamma*(r2-r3)/(gamma-1)) /(math.sqrt(53.3*T/32.2))\n", + "\n", + "#result\n", + "print \"Exit velocity = %d ft/sec\" %V2\n", + "print \"Mass flow rate = \", round(wdot, 3), \"lbm/sec\"\n" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "Exit velocity = 2196 ft/sec\n", + "Mass flow rate = 1.107 lbm/sec\n" + ] + } + ], + "prompt_number": 2 + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Example 11.3, page no. 212" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "\n", + "import math\n", + "\n", + "#initialization\n", + "Pt1 = 100.0 #lb/in^2\n", + "Tt1 = 960.0 #RP2 = 15 #lb/in^2\n", + "wdot = 1.13 #lbm/sec\n", + "gamma = 1.4\n", + "\n", + "#calculation\n", + "Pstar = Pt1*(2/(1+gamma))**(gamma/(gamma-1))\n", + "Tstar = Tt1*(2/(1+gamma))\n", + "Vstar = math.sqrt(gamma*32.2*53.3*Tstar)\n", + "vstar = 53.3*Tstar/(144*Pstar)\n", + "Astar = wdot*vstar*144/Vstar\n", + "\n", + "#result\n", + "print \"Ideal throat area = \", round(Astar,3), \"in^2\"\n", + "print \"Ideal pressure = \", round(Pstar, 1), \"lb/in^2\"\n", + "print \"Ideal temperature = %d R\" %Tstar\n", + "print \"Ideal throat specific volume = \", round(vstar, 1), \"ft^3/lbm\"\n" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "Ideal throat area = 0.658 in^2\n", + "Ideal pressure = 52.8 lb/in^2\n", + "Ideal temperature = 800 R\n", + "Ideal throat specific volume = 5.6 ft^3/lbm\n" + ] + } + ], + "prompt_number": 7 + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Example 11.4, page no. 215" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "\n", + "import math\n", + "\n", + "\n", + "#initialization\n", + "ht1 = 1329.1\n", + "st1 = 1.7581\n", + "h2s = 1151.4\n", + "s2s = 1.7581\n", + "\n", + "#calculation\n", + "eta = math.sqrt((ht1-1192.8)/(ht1-h2s))\n", + "\n", + "#result\n", + "print \"efficiency = \", round(eta, 2)\n" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "efficiency = 0.88\n" + ] + } + ], + "prompt_number": 10 + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Example 11.5, page no. 216" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "\n", + "#initializaiton\n", + "v = 2200.0 #exit velocity from ex. 11.2\n", + "p = 15.0 #exit pressure\n", + "n_eta = 0.95 #nozzle efficiency 95%\n", + "t2 = 598.0\n", + "\n", + "#calculations\n", + "V2 = n_eta*v\n", + "v = (53.3*t2)/(144.0*p)\n", + "w = (1.0*V2)/(144.0*v)\n", + "\n", + "print \"Volume at exit \", round(v, 1), \"ft^3/lbm\"\n", + "print \"The mass flow is \", round(w, 3), \"lbm/sec\"\n", + "#difference in answers due to rounding off in Python, check manually" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "Volume at exit 14.8 ft^3/lbm\n", + "The mass flow is 0.984 lbm/sec\n" + ] + } + ], + "prompt_number": 10 + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Example 11.6, page no. 219" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "\n", + "#initialization\n", + "v = 500.0 #ft/sec\n", + "P = 14.7 #lb/in^2\n", + "T = 60+460.0 #R\n", + "eta = 0.85\n", + "cp = 0.24\n", + "gamma = 1.4\n", + "\n", + "#calculation\n", + "Pt2 = eta*P*(1+ (gamma-1)*v**2 /(2*gamma*32.2*53.3*T))**(gamma/(gamma-1))\n", + "Tratio = 1+(gamma-1)*v*v/(2*gamma*32.2*53.3*T)\n", + "Tt2 = T*Tratio\n", + "\n", + "#result\n", + "print \"Exit stagnation temperature = %d R\" %(Tt2+1)\n" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "Exit stagnation temperature = 541 R\n" + ] + } + ], + "prompt_number": 19 + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Example 11.7, page no. 222" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "\n", + "import math\n", + "\n", + "#initialization\n", + "P = 30.0 #lb/in^2\n", + "T = 1000+460.0 #R\n", + "Pd = 14.7 #lb/in^2\n", + "w = 60.0 #lbm/sec\n", + "eta = 0.95 #percent\n", + "R = 53.3\n", + "gamma = 1.35\n", + "cp = 0.264\n", + "\n", + "#calculation\n", + "V2s = math.sqrt(2*gamma*32.2*53.3*T*(1-(Pd/P)**(0.259))/(gamma-1))\n", + "V2 = eta*V2s\n", + "Fn = w*(V2)/32.2\n", + "\n", + "#result\n", + "print \"Thrust of the engine = %d ft/sec\" %Fn\n", + "\n", + "#difference due to +5 in V2s calculation while sqrt" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "Thrust of the engine = 3196 ft/sec\n" + ] + } + ], + "prompt_number": 1 + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Example 11.8, page no. 226" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "\n", + "import math\n", + "\n", + "#initialization\n", + "v = 600.0 #ft/sec\n", + "T = 60+460.0 #R\n", + "P = 14.7 #lb/in^2\n", + "Pratio = 6.0\n", + "Tin = 1540+460.0 #R\n", + "cp = 0.264\n", + "cpratio = 1.35\n", + "\n", + "#calculation\n", + "Pt2byP1 = (1+(cpratio-1)*v**2/(cpratio*2*32.2*53.3*T))**(3.86)\n", + "Pt3byP1 = Pt2byP1*Pratio\n", + "eta = 1-1/(Pt3byP1)**0.259\n", + "Tt3 = T*(Pt3byP1)**((cpratio-1)/cpratio)\n", + "Q = cp*(Tin-Tt3)\n", + "V6 = math.sqrt(eta*2*32.2*778*Q + v**2)\n", + "Fn = (V6-v)/32.2\n", + "\n", + "#resullts\n", + "print \"Thermal efficiency = \", round(eta, 3)\n", + "print \"thrust per pound of air per sec = \", round(Fn, 1), \"lb-sec/lbm\"" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "Thermal efficiency = 0.403\n", + "thrust per pound of air per sec = 59.8 lb-sec/lbm\n" + ] + } + ], + "prompt_number": 27 + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Example 11.9, page no. 229" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "\n", + "#initialization\n", + "V = 1000.0 #mph\n", + "P = 14.7 #lb/in^2\n", + "T = 60.0 #F\n", + "g = 1.4\n", + "\n", + "#calculation\n", + "\n", + "V1 = V*(88/T)\n", + "Pratio = (1+ (g-1)*V1**2 /(2*g*32.2*53.3*(T+460)))**(g/(g-1))\n", + "eta = 1-1/(Pratio)**0.286\n", + "\n", + "#result\n", + "print \"Theoretical cycle efficiency = \", round(eta, 3)" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "Theoretical cycle efficiency = 0.256\n" + ] + } + ], + "prompt_number": 29 + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Example 11.10, page no. 230" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "\n", + "import math\n", + "\n", + "#initialization\n", + "P = 300.0 #lb/in^2\n", + "P2 = 14.7 #lb/in^2\n", + "T = 4540+460.0 #R\n", + "w = 100.0 #lbm/sec\n", + "g = 1.25\n", + "MW = 30.0\n", + "R = 1544.0\n", + "\n", + "#calculation\n", + "R = R/MW\n", + "Pratio = P2/P\n", + "V4 = math.sqrt(2*g*32.2*51.5*T*(1-(Pratio)**((g-1)/g))/(g-1)) \n", + "Fn = w*V4/32.2\n", + "\n", + "#result\n", + "print \"Thrust = %d lb\" %Fn" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "Thrust = 19031 lb\n" + ] + } + ], + "prompt_number": 30 + } + ], + "metadata": {} + } + ] +}
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