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diff --git a/Fluid_Mechanics_by_John_F._Douglas/Chapter_12.ipynb b/Fluid_Mechanics_by_John_F._Douglas/Chapter_12.ipynb
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+{
+ "metadata": {
+  "name": "",
+  "signature": "sha256:24438326f2aac267ced1e2e3aa21e094819eefb50d5f8862608b62208400992d"
+ },
+ "nbformat": 3,
+ "nbformat_minor": 0,
+ "worksheets": [
+  {
+   "cells": [
+    {
+     "cell_type": "heading",
+     "level": 1,
+     "metadata": {},
+     "source": [
+      "Chapter 12: Incompressible Flow around a Body"
+     ]
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Example 12.1, Page 399"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from __future__ import division\n",
+      "import math\n",
+      "\n",
+      "\n",
+      " #Initializing  the  variables\n",
+      "x  =35;\n",
+      "T  =  50;\n",
+      "m  =  1;\n",
+      "g  =9.81;\n",
+      "rho  =  1.2;\n",
+      "A  =  1.2;\n",
+      "U0  =  40*1000/3600;                                            #  Velocity  in  m/s\n",
+      "\n",
+      " #Calculations\n",
+      "L  =  T*math.sin(math.radians(x))+m*g;\n",
+      "D  =T*math.cos(math.radians(x));\n",
+      "Cl  =  2*L/(rho*U0**2*A);\n",
+      "Cd  =  2*D/(rho*U0**2*A);  \n",
+      "\n",
+      "print \"Lift Coefficient :\",round(Cl,3)\n",
+      "print \"Drag Coefficient :\",round(Cd,3)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "Lift Coefficient : 0.433\n",
+        "Drag Coefficient : 0.461\n"
+       ]
+      }
+     ],
+     "prompt_number": 1
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Example 12.2, Page 406"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from __future__ import division\n",
+      "import math\n",
+      "\n",
+      "\n",
+      " #Initializing  the  variables\n",
+      "Vp  =12;\n",
+      "lp  =  40;\n",
+      "lm  =  1;\n",
+      "As  =  2500;\n",
+      "Dm  =  32;\n",
+      "rhoP  =  1025;\n",
+      "rhoM  =  1000;\n",
+      "Ap  =  As;\n",
+      "\n",
+      " #Calculations\n",
+      "Am  =  As/40**2;\n",
+      "Vm  =  round(Vp*(lm/lp)**0.5,2);\n",
+      "Dfm  =  round(3.7*Vm**1.95*Am,1);\n",
+      "Rm  =  Dm  -  Dfm;\n",
+      "Rp  =  Rm  *(rhoP/rhoM)*(lp/lm)**2*(Vp/Vm)**2;\n",
+      "Dfp  =  2.9*Vp**1.8*Ap;\n",
+      "Dp  =  Rp  +  Dfp;\n",
+      "\n",
+      "print \"Expected total resistance (kN) :\",round(Dp/1000,2)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "Expected total resistance (kN) : 1407.07\n"
+       ]
+      }
+     ],
+     "prompt_number": 2
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Example 12.3, Page 410"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from __future__ import division\n",
+      "import math\n",
+      "\n",
+      "\n",
+      " #Initializing  the  variables\n",
+      "U0  =  80*1000/3600;\n",
+      "d  =  0.02;\n",
+      "rho  =1.2;\n",
+      "mu  =  1.7*10**-5;\n",
+      "A  =  0.02*500;                            #  Projected  area  of  wire\n",
+      "N  =  20;                                  #  No  of  cables\n",
+      "\n",
+      " #Calculations\n",
+      "Re  =  rho*U0*d/mu;\n",
+      "Cd  =  1.2                                 #  From  figure  12.10  for  given  Re;  \n",
+      "D  =  0.5*rho*Cd*A*U0**2\n",
+      "F  =  N*D;  \n",
+      "f  =    0.198*(U0/d)*(1-19.7/Re);\n",
+      "\n",
+      "print \"Total force on tower (kN) :\",round(F/1000,2)\n",
+      "print \"Frequency (Hz)            :\",round(f,1)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "Total force on tower (kN) : 71.11\n",
+        "Frequency (Hz)            : 219.9\n"
+       ]
+      }
+     ],
+     "prompt_number": 3
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Example 12.4, Page 415"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from __future__ import division\n",
+      "import math\n",
+      "\n",
+      "\n",
+      " #Initializing  the  variables\n",
+      "mu  =  0.03;\n",
+      "d  =  10**-3;\n",
+      "rhoP  =  1.1*10**3;\n",
+      "g  =  9.81;\n",
+      "rho0  =  0.9*10**3;\n",
+      " #Calculations\n",
+      "B  =  18*mu/(d**2*rhoP);\n",
+      "t  =  round(4.60/B,4);\n",
+      "Vt  =  round(d**2*(rhoP  -  rho0)*g/(18*mu),5);\n",
+      "Re  =  rho0*Vt*d/mu;\n",
+      "\n",
+      "print \"Time taken by the particle take to reach 99 per cent of its terminal velocity (s):\",t\n",
+      "print \"\\nReynolds No corrosponding to the velocity :\",Re"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "Time taken by the particle take to reach 99 per cent of its terminal velocity (s): 0.0094\n",
+        "\n",
+        "Reynolds No corrosponding to the velocity : 0.1089\n"
+       ]
+      }
+     ],
+     "prompt_number": 4
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Example 12.5, Page 417"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from __future__ import division\n",
+      "import math\n",
+      "\n",
+      "\n",
+      " #Initializing  the  variables\n",
+      "muO  =  0.0027;\n",
+      "Vt  =  3*10**-3;\n",
+      "rhoW  =  1000;\n",
+      "rhoP  =  2.4*rhoW;\n",
+      "rhoO  =  0.9*rhoW;\n",
+      "g  =  9.81;\n",
+      "muA  =  1.7*10**-5;\n",
+      "rhoA  =  1.3;\n",
+      "\n",
+      " #Calculations\n",
+      "d  =  (18*muO*Vt/(rhoP-rhoO)/g)**0.5;\n",
+      "Re  =  Vt*d*rhoO/muO;\n",
+      "\n",
+      " #Movement  of  particle  in  upward  direction\n",
+      "if(Re < 1):\n",
+      "    v  =  0.5;\n",
+      "    \n",
+      "    Re=5;       #  from  fig  12.15\n",
+      "    vt  =  muA*Re/(rhoA*d);\n",
+      "    u  =  vt+v;\n",
+      "    print \"Velocity of air stream blowing vertically up (m/s) :\",round(u,3) \n",
+      "else:\n",
+      "    print \"strokes law is not valid\""
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "Velocity of air stream blowing vertically up (m/s) : 1.157\n"
+       ]
+      }
+     ],
+     "prompt_number": 5
+    },
+    {
+     "cell_type": "heading",
+     "level": 2,
+     "metadata": {},
+     "source": [
+      "Example 12.6, Page 429"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "from __future__ import division\n",
+      "import math\n",
+      "\n",
+      "\n",
+      " #Initializing  the  variables\n",
+      "c  =  2;\n",
+      "s  =  10;\n",
+      "rho  =  5.33;\n",
+      "rho_ellip  =  1.2;\n",
+      "D  =  400;\n",
+      "L  =  45000;\n",
+      "scale  =  20;\n",
+      "U_windTunnel  =  500;\n",
+      "U_proto  =  400*1000/3600;\n",
+      "\n",
+      " #Calculations\n",
+      "A  =  c*s;\n",
+      "U_model  =  U_windTunnel/scale;\n",
+      "Cd  =  D/(0.5*rho*U_model**2*A);\n",
+      "Cl  =  L/(0.5*rho_ellip*U_proto**2*A);          #  Considering  elliptical  Lift  model\n",
+      "Cdi  =  Cl**2/(math.pi*s/c);                    #  Aspect  Ratio  =    s/c  \n",
+      "Cdt  =  Cd  +  Cdi;\n",
+      "Dw  =  0.5*Cdt*rho_ellip*U_proto**2*A;\n",
+      "print \"Total drag on full sized wing (kN) :\",round(Dw/1000,2)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "Total drag on full sized wing (kN) : 2.65\n"
+       ]
+      }
+     ],
+     "prompt_number": 6
+    }
+   ],
+   "metadata": {}
+  }
+ ]
+}
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