diff options
Diffstat (limited to 'Aircraft_Propulsion_by__S._Farokhi/Chapter3.ipynb')
| -rwxr-xr-x | Aircraft_Propulsion_by__S._Farokhi/Chapter3.ipynb | 240 |
1 files changed, 0 insertions, 240 deletions
diff --git a/Aircraft_Propulsion_by__S._Farokhi/Chapter3.ipynb b/Aircraft_Propulsion_by__S._Farokhi/Chapter3.ipynb deleted file mode 100755 index 803eff7e..00000000 --- a/Aircraft_Propulsion_by__S._Farokhi/Chapter3.ipynb +++ /dev/null @@ -1,240 +0,0 @@ -{
- "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 |