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-{
- "metadata": {
- "name": "",
- "signature": "sha256:9400ac9019314c4e9a568a522343f0bdbb2a3d098bb24add69a9bd20d9589ad0"
- },
- "nbformat": 3,
- "nbformat_minor": 0,
- "worksheets": [
- {
- "cells": [
- {
- "cell_type": "heading",
- "level": 1,
- "metadata": {},
- "source": [
- "Chapter 13: Gas Dynamics"
- ]
- },
- {
- "cell_type": "heading",
- "level": 2,
- "metadata": {},
- "source": [
- "Example 13.1, page no. 259"
- ]
- },
- {
- "cell_type": "code",
- "collapsed": false,
- "input": [
- "\n",
- "import math\n",
- "\n",
- "#initialization\n",
- "v = 2000.0 #ft/sec\n",
- "P = 14.7 #lb/in^2\n",
- "g = 1.4\n",
- "T = 10+460.0 #R\n",
- "\n",
- "#calculation\n",
- "c = math.sqrt(g*32.2*53.3*T)\n",
- "Nm = v/c\n",
- "Tratio = 1+ (g-1)/2 *Nm**2\n",
- "Tt = Tratio*T\n",
- "Pratio = (Tratio)**(g/(g-1))\n",
- "Pt = Pratio*P\n",
- "\n",
- "#result\n",
- "print \"Stagnation temperature = %d R\" %Tt\n",
- "print \"Stagnation pressure = \", round(Pt, 1), \"lb/in^2\""
- ],
- "language": "python",
- "metadata": {},
- "outputs": [
- {
- "output_type": "stream",
- "stream": "stdout",
- "text": [
- "Stagnation temperature = 802 R\n",
- "Stagnation pressure = 95.8 lb/in^2\n"
- ]
- }
- ],
- "prompt_number": 2
- },
- {
- "cell_type": "heading",
- "level": 2,
- "metadata": {},
- "source": [
- "Example 13.2, page no. 261"
- ]
- },
- {
- "cell_type": "code",
- "collapsed": false,
- "input": [
- "\n",
- "import math\n",
- "\n",
- "#initialization\n",
- "A = 0.3 #ft^2\n",
- "P = 30.0 #lb/in^2\n",
- "T = 160+460.0 #R\n",
- "Mn = 0.82\n",
- "g = 1.4\n",
- "\n",
- "#calculation\n",
- "w = A*144*P*math.sqrt(g*32.2) *Mn*(1+ (g-1)/2.0 *(Mn)**2)**(-3)/math.sqrt(53.3*T)\n",
- "\n",
- "#result\n",
- "print \"Mass flow = \", round(w, 1), \"lbm/sec\""
- ],
- "language": "python",
- "metadata": {},
- "outputs": [
- {
- "output_type": "stream",
- "stream": "stdout",
- "text": [
- "Mass flow = 26.9 lbm/sec\n"
- ]
- }
- ],
- "prompt_number": 3
- },
- {
- "cell_type": "heading",
- "level": 2,
- "metadata": {},
- "source": [
- "Example 13.3, page no. 263"
- ]
- },
- {
- "cell_type": "code",
- "collapsed": false,
- "input": [
- "\n",
- "import math\n",
- "\n",
- "#initialization\n",
- "Mn = 3.0\n",
- "Mni = 0.2\n",
- "w = 10.0 #lbm/sec\n",
- "g = 1.4\n",
- "P = 200.0 #lb/in^2\n",
- "T = 400+460.0 #R\n",
- "\n",
- "#calculation\n",
- "Astar = w*math.sqrt(53.3*T) *((g+1)/2)**3 /(P*math.sqrt(g*32.2))\n",
- "A1ratio = (2.0/(g+1) + (g-1)*Mni**2 /(g+1))**3 /Mni\n",
- "A1 = A1ratio*Astar\n",
- "A2ratio = (2.0/(g+1) + (g-1)*Mn**2 /(g+1))**3 /Mn\n",
- "A2 = A2ratio*Astar\n",
- "Pexit = P/(1+ Mni*Mn**2)**(g/(g-1))\n",
- "\n",
- "#result\n",
- "print \"Throat Area = \", round(Astar, 2), \"in^2\"\n",
- "print \"Inlet Area = \", round(A1, 2), \"in^2\"\n",
- "print \"Exit Area = \", round(A2, 2), \"in^2\"\n",
- "print \"Exit pressure = \", round(Pexit, 2), \"lb/in^2\""
- ],
- "language": "python",
- "metadata": {},
- "outputs": [
- {
- "output_type": "stream",
- "stream": "stdout",
- "text": [
- "Throat Area = 2.76 in^2\n",
- "Inlet Area = 8.16 in^2\n",
- "Exit Area = 11.67 in^2\n",
- "Exit pressure = 5.44 lb/in^2\n"
- ]
- }
- ],
- "prompt_number": 4
- },
- {
- "cell_type": "heading",
- "level": 2,
- "metadata": {},
- "source": [
- "Example 13.4, page no. 266"
- ]
- },
- {
- "cell_type": "code",
- "collapsed": false,
- "input": [
- "\n",
- "import math\n",
- "\n",
- "#initialization\n",
- "Pi = 750.0 #lb/in^2\n",
- "g = 1.25\n",
- "TA = 2.0 #in^2\n",
- "r = 3.0\n",
- "\n",
- "#calculation\n",
- "Fstar = round(((g+1)*(2.0/(g+1))**5 *TA*750))\n",
- "Me = 2.45\n",
- "Fratio = round(((1+g*Me**2)/(Me*(math.sqrt(4.5+ (g**2 -1)*Me**2)))), 3)\n",
- "F2 = Fratio*Fstar\n",
- "Pratio = (1+ 0.2*Me**2)**5\n",
- "Fnstar = Fratio-((g+1)/2.0)**5 *r/(Pratio*2.25)\n",
- "Fn = Fnstar*Fstar\n",
- "\n",
- "#result\n",
- "print \"Internal rocket thrust = %d lb\" %F2 #answer in textbook is wrong\n",
- "print \"External thrust = %d lb\" %Fn #answer in textbook is wrong"
- ],
- "language": "python",
- "metadata": {},
- "outputs": [
- {
- "output_type": "stream",
- "stream": "stdout",
- "text": [
- "Internal rocket thrust = 2316 lb\n",
- "External thrust = 2229 lb\n"
- ]
- }
- ],
- "prompt_number": 13
- },
- {
- "cell_type": "heading",
- "level": 2,
- "metadata": {},
- "source": [
- "Example 13.5, page no. 270"
- ]
- },
- {
- "cell_type": "code",
- "collapsed": false,
- "input": [
- "\n",
- "#initialization\n",
- "Tt2 = 1620+460 #R\n",
- "Tt1 = 60+460 #R\n",
- "Mi = 0.2\n",
- "P = 40 #lb/in^2\n",
- "g = 1.35\n",
- "\n",
- "#calculation\n",
- "Tratio = Tt2/Tt1\n",
- "#From figure\n",
- "fM = 4*0.036\n",
- "NM2 = 0.49\n",
- "Pratio = 0.98/0.885\n",
- "Pt2 = P/Pratio\n",
- "\n",
- "#result\n",
- "print \"Final stagnation pressure = \", round(Pt2, 1), \"lb/in^2\"\n",
- "print \"Final mach number = \", round(fM, 3)"
- ],
- "language": "python",
- "metadata": {},
- "outputs": [
- {
- "output_type": "stream",
- "stream": "stdout",
- "text": [
- "Final stagnation pressure = 36.1 lb/in^2\n",
- "Final mach number = 0.144\n"
- ]
- }
- ],
- "prompt_number": 16
- },
- {
- "cell_type": "heading",
- "level": 2,
- "metadata": {},
- "source": [
- "Example 13.6, page no. 273"
- ]
- },
- {
- "cell_type": "code",
- "collapsed": false,
- "input": [
- "\n",
- "#initialization\n",
- "M = 0.4\n",
- "l = 10.0 #ft\n",
- "dia = 3.0 #in\n",
- "P = 50.0 #lb/in^2\n",
- "ff = 0.008\n",
- "T = 100+460.0 #R\n",
- "\n",
- "#calculation\n",
- "constant = 4*ff*l/dia\n",
- "exitM = 2.9-constant\n",
- "Nm2 = 0.5\n",
- "Ptratio = 2.73/2.3\n",
- "Pt2 = P/Ptratio\n",
- "\n",
- "#result\n",
- "print \"Exit total pressure = \", round(Pt2, 1), \"lb/in^2\""
- ],
- "language": "python",
- "metadata": {},
- "outputs": [
- {
- "output_type": "stream",
- "stream": "stdout",
- "text": [
- "Exit total pressure = 42.1 lb/in^2\n"
- ]
- }
- ],
- "prompt_number": 17
- }
- ],
- "metadata": {}
- }
- ]
-} \ No newline at end of file
generated by cgit (git 2.34.1) at 2025-01-23 15:59:40 +0000