summaryrefslogtreecommitdiff
path: root/Thermodynamics_by_F_P_Durham/chapter11.ipynb
diff options
context:
space:
mode:
Diffstat (limited to 'Thermodynamics_by_F_P_Durham/chapter11.ipynb')
-rwxr-xr-xThermodynamics_by_F_P_Durham/chapter11.ipynb484
1 files changed, 0 insertions, 484 deletions
diff --git a/Thermodynamics_by_F_P_Durham/chapter11.ipynb b/Thermodynamics_by_F_P_Durham/chapter11.ipynb
deleted file mode 100755
index ddbbdc4c..00000000
--- a/Thermodynamics_by_F_P_Durham/chapter11.ipynb
+++ /dev/null
@@ -1,484 +0,0 @@
-{
- "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": {}
- }
- ]
-} \ No newline at end of file
generated by cgit (git 2.34.1) at 2025-01-23 15:43:05 +0000