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_by__S._Farokhi/Chapter3.ipynb | 240 ++++++++++++++++++++++
 1 file changed, 240 insertions(+)
 create mode 100755 Aircraft_Propulsion_by__S._Farokhi/Chapter3.ipynb

(limited to 'Aircraft_Propulsion_by__S._Farokhi/Chapter3.ipynb')

diff --git a/Aircraft_Propulsion_by__S._Farokhi/Chapter3.ipynb b/Aircraft_Propulsion_by__S._Farokhi/Chapter3.ipynb
new file mode 100755
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@@ -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