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diff --git a/Aircraft_Structures_for_Engineering_Students/Chapter15.ipynb b/Aircraft_Structures_for_Engineering_Students/Chapter15.ipynb
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+{
+ "metadata": {
+  "name": "",
+  "signature": "sha256:1bd6512f5b9ca8155cc1e9c3b04ad8207681499e095afaf4830a217017e989ea"
+ },
+ "nbformat": 3,
+ "nbformat_minor": 0,
+ "worksheets": [
+  {
+   "cells": [
+    {
+     "cell_type": "heading",
+     "level": 1,
+     "metadata": {},
+     "source": [
+      "Chapter 15: Fatigue"
+     ]
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Example 15.1 Pg.No.445"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from __future__ import division\n",
+      "from scipy import integrate\n",
+      "from sympy import symbols\n",
+      "import math\n",
+      "\n",
+      "#eqn 15.30 K=S(pi*a)^1/2*alpha\n",
+      "S=175         #stress range (N/mm^2)\n",
+      "K=1708          #fracture toughness (n/mm^3/2)\n",
+      "alpha=1         #constant\n",
+      "n=4         #constant\n",
+      "C=40*10**-15      #rate of crack growth (mm/cycle)\n",
+      "ai=0.1            #initial crack length\n",
+      "\n",
+      "alpha_f=K**2/S**2/math.pi\n",
+      "\n",
+      "\n",
+      "Nf=2/C/(n-2)/(S*math.pi**0.5)**n*(1/ai**((n-2)/2)-1/alpha_f**((n-2)/2))\n",
+      "print \"Number of cycles to failure = %5.0f cycles\\n\"%(Nf)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "Number of cycles to failure = 26919 cycles\n",
+        "\n"
+       ]
+      }
+     ],
+     "prompt_number": 4
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [],
+     "language": "python",
+     "metadata": {},
+     "outputs": []
+    }
+   ],
+   "metadata": {}
+  }
+ ]
+}
+\ No newline at end of file