From 47d7279a724246ef7aa0f5359cf417992ed04449 Mon Sep 17 00:00:00 2001 From: hardythe1 Date: Wed, 3 Jun 2015 15:27:17 +0530 Subject: add books --- Aircraft_Propulsion/Chapter3.ipynb | 240 +++++++++++++++++++++++++++++++++++++ 1 file changed, 240 insertions(+) create mode 100755 Aircraft_Propulsion/Chapter3.ipynb (limited to 'Aircraft_Propulsion/Chapter3.ipynb') diff --git a/Aircraft_Propulsion/Chapter3.ipynb b/Aircraft_Propulsion/Chapter3.ipynb new file mode 100755 index 00000000..803eff7e --- /dev/null +++ b/Aircraft_Propulsion/Chapter3.ipynb @@ -0,0 +1,240 @@ +{ + "metadata": { + "name": "", + "signature": "sha256:c3d58d095c748f580c55e0c0973b03d491cabb5f398c413d6d8d00dcbb57dc20" + }, + "nbformat": 3, + "nbformat_minor": 0, + "worksheets": [ + { + "cells": [ + { + "cell_type": "heading", + "level": 1, + "metadata": {}, + "source": [ + "Chapter3-Engine thurst performance parameters" + ] + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Ex1-pg101" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "import math\n", + "#calculate The ram drag for given engine in kN\n", + "M0=0.85 ##Mach no.\n", + "a0=300. ##speed of sound in m/s\n", + "m=50. ##Air mass flow rate in kg/s\n", + "##Calculations\n", + "V0=M0*a0 ##Flight speed\n", + "Dr=m*V0 ##Ram drag\n", + "Dk=Dr/1000. ##in kN\n", + "print'%s %.2f %s'%(\"The ram drag for given engine in kN:\",Dk,\"\")" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "The ram drag for given engine in kN: 12.75 \n" + ] + } + ], + "prompt_number": 1 + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Ex2-pg102" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "#calculate gross thurst of the core and fan nozzles\n", + "\n", + "Cv=450. ##exhaust velocity at core in m/s\n", + "Nv=350. ##exhaust velocity at nozzle in m/s\n", + "Cm=50. ##Mass flow rate through core in kg/s\n", + "Nm=350. ##Mass flow rate through nozzle in kg/s\n", + "##Calculations:\n", + "##Newton's second law\n", + "Fgc=Cm*Cv ##gross thrust of the core\n", + "Fgf=Nm*Nv ##gross thrust of the nozzle fan\n", + "print'%s %.f %s'%(\"Gross thrust of the core in\",Fgc,\"N\")\n", + "print'%s %.f %s'%(\"Gross thrust of the fan nozzles in\",Fgf,\"N\")\n" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "Gross thrust of the core in 22500 N\n", + "Gross thrust of the fan nozzles in 122500 N\n" + ] + } + ], + "prompt_number": 3 + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Ex3-pg111" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "import math\n", + "#calculate The rocket gross thrust and pressure thurst\n", + "V9=4000 ##in m/s\n", + "p9=200*10**3 ##in Pa\n", + "p0=100*10**3 ## in Pa\n", + "D=2. ##in meter\n", + "m=200.+50. ## in kg/s\n", + "A=math.pi*(D**2)/4. ##nozzle exit area\n", + "##let p=(p9-p0)*A i.e. pressure thrust\n", + "p=(p9-p0)*A\n", + "mt=m*V9 ##momentum thrust.\n", + "t=p+mt ##rocket gross thrust\n", + "print'%s %.2f %s'%(\"The pressure thrust in\",p,\"N\")\n", + "print'%s %.1f %s'%(\"The rocket gross thrust in\",t,\"N\")" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "The pressure thrust in 314159.27 N\n", + "The rocket gross thrust in 1314159.3 N\n" + ] + } + ], + "prompt_number": 5 + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Ex4-pg114" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "import math\n", + "#calcualte engine thurst takeoff\n", + "m0=100. ##air flow rate in kg/s\n", + "V0=0. ##takeoff assumptions in m/s\n", + "mf=2. ##2% of fuel-to-air ratio\n", + "Qr=43000. ##Heating value of typical hydrocarbon fuel in kJ/kg\n", + "V9=900. ##high speed exhaust jet (in m/s)\n", + "e=((m0+mf)*(V9)**2.)/(2.*(mf)*(Qr)*1000.)\n", + "m9=m0+mf\n", + "t=m9*V9 ## the engine thrust at takeoff.\n", + "print'%s %.f %s'%(\"The engine thrust at takeoff in SI units\",t,\"N\")" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "The engine thrust at takeoff in SI units 91800 N\n" + ] + } + ], + "prompt_number": 7 + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Ex5-pg117" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "#calculate the Engine propulsive efficiency\n", + "V9=900. ## in m/s\n", + "V0=200. ## in m/s\n", + "e=2./(1.+(V9/V0))\n", + "print'%s %.7f %s'%(\"Engine propulsive efficiency\",e,\"\")" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "Engine propulsive efficiency 0.3636364 \n" + ] + } + ], + "prompt_number": 9 + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Ex6-pg118" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "#estimate Propulsive efficiency\n", + "import math\n", + "V9=250. ##in m/s\n", + "V0=200. ##in m/s\n", + "##Calculations:\n", + "e=2./(1.+(V9/V0))\n", + "print'%s %.3f %s'%(\"Propulsive efficiency:\",e,\"\")" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "Propulsive efficiency: 0.889 \n" + ] + } + ], + "prompt_number": 8 + } + ], + "metadata": {} + } + ] +} \ No newline at end of file -- cgit