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diff --git a/Aircraft_Propulsion_by__S._Farokhi/Chapter3_1.ipynb b/Aircraft_Propulsion_by__S._Farokhi/Chapter3_1.ipynb new file mode 100755 index 00000000..9b328651 --- /dev/null +++ b/Aircraft_Propulsion_by__S._Farokhi/Chapter3_1.ipynb @@ -0,0 +1,240 @@ +{
+ "metadata": {
+ "name": "",
+ "signature": "sha256:e5ce604b49bc138fd65826c495598b13c742523cc595beeb292a2a1aa22f7c49"
+ },
+ "nbformat": 3,
+ "nbformat_minor": 0,
+ "worksheets": [
+ {
+ "cells": [
+ {
+ "cell_type": "heading",
+ "level": 1,
+ "metadata": {},
+ "source": [
+ "Chapter3-Engine Thrust and 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": {}
+ }
+ ]
+}
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