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-{
- "metadata": {
-  "name": "",
-  "signature": "sha256:ac94f65c54c89da6d7a90bae31a6309586e55713ceeeb8cf1cb6a41246a395ce"
- },
- "nbformat": 3,
- "nbformat_minor": 0,
- "worksheets": [
-  {
-   "cells": [
-    {
-     "cell_type": "heading",
-     "level": 1,
-     "metadata": {},
-     "source": [
-      "CHAPTER18:LAMINAR BOUNDARY LAYERS"
-     ]
-    },
-    {
-     "cell_type": "heading",
-     "level": 2,
-     "metadata": {},
-     "source": [
-      "Example E01 : Pg 595"
-     ]
-    },
-    {
-     "cell_type": "code",
-     "collapsed": false,
-     "input": [
-      "# All the quantities are expressed in SI units\n",
-      "import math \n",
-      "from math import sqrt\n",
-      "p_inf = 101000.;                    # freestream pressure\n",
-      "T_inf = 288.;                       # freestream temperature\n",
-      "c = 2.;                             # chord length of the plate\n",
-      "S = 40.;                            # planform area of the plate\n",
-      "mue_inf=1.7894*10.**5.;               # coefficient of viscosity at sea level\n",
-      "gam=1.4;                         # ratio of specific heats\n",
-      "R=287.;                           # specific gas constant\n",
-      "# the freestream density is\n",
-      "rho_inf = p_inf/R/T_inf;\n",
-      "# the speed of sound is\n",
-      "a_inf = sqrt(gam*R*T_inf);\n",
-      "# (a)\n",
-      "V_inf = 100.;\n",
-      "# thus the mach number can be calculated as\n",
-      "M_inf = V_inf/a_inf;\n",
-      "# the Reynolds number at the trailing is given as\n",
-      "Re_c = rho_inf*V_inf*c/mue_inf;\n",
-      "# from eq.(18.22)\n",
-      "Cf = 1.328/sqrt(Re_c);\n",
-      "# the friction drag on one surface of the plate is given by\n",
-      "D_f = 1./2.*rho_inf*V_inf**2.*S*Cf;\n",
-      "# the total drag generated due to both surfaces is\n",
-      "D = 2.*D_f;\n",
-      "print\"The total frictional drag is:(a)D =\",D,\"N\"\n",
-      "# (b)\n",
-      "V_inf = 1000.;\n",
-      "# thus the mach number can be calculated as\n",
-      "M_inf = V_inf/a_inf;\n",
-      "# the Reynolds number at the trailing is given as\n",
-      "Re_c = rho_inf*V_inf*c/mue_inf;\n",
-      "# from eq.(18.22)\n",
-      "Cf = 1.2/sqrt(Re_c);\n",
-      "# the friction drag on one surface of the plate is given by\n",
-      "D_f = 1./2.*rho_inf*V_inf**2.*S*Cf;\n",
-      "# the total drag generated due to both surfaces is\n",
-      "D = 2.*D_f;\n",
-      "print\"(b) D =\",D,\"N\""
-     ],
-     "language": "python",
-     "metadata": {},
-     "outputs": [
-      {
-       "output_type": "stream",
-       "stream": "stdout",
-       "text": [
-        "The total frictional drag is:(a)D = 17563872.6566 N\n",
-        "(b) D = 501884115.614 N\n"
-       ]
-      }
-     ],
-     "prompt_number": 1
-    },
-    {
-     "cell_type": "heading",
-     "level": 2,
-     "metadata": {},
-     "source": [
-      "Example E02 : Pg 596"
-     ]
-    },
-    {
-     "cell_type": "code",
-     "collapsed": false,
-     "input": [
-      "# All the quantities are expressed in SI units\n",
-      "import math \n",
-      "from math import sqrt\n",
-      "Pr = 0.71;                    # Prandlt number of air at standard conditions\n",
-      "Pr_star = Pr;\n",
-      "Te = 288.;                     # temperature of the upper plate\n",
-      "ue = 1000.;                    # velocity of the upper plate\n",
-      "Me = 2.94;                    # Mach number of flow on the upper plate\n",
-      "p_star = 101000.;\n",
-      "R = 287.;                      # specific gas constant\n",
-      "T0 = 288.;                     # reference temperature at sea level\n",
-      "mue0 = 1.7894*10**-5;             # reference viscosity at sea level\n",
-      "c = 2.;                        # chord length of the plate\n",
-      "S = 40.;                       # plate planform area\n",
-      "\n",
-      "# recovery factor for a boundary layer is given by eq.(18.47) as\n",
-      "r = sqrt(Pr);\n",
-      "\n",
-      "# rearranging eq.(16.49), we get for M = 2.94\n",
-      "T_aw = Te*(1+r*(2.74-1));\n",
-      "\n",
-      "# from eq.(18.53)\n",
-      "T_star = Te*(1 + 0.032*Me**2. + 0.58*(T_aw/Te-1.));\n",
-      "\n",
-      "# from the equation of state\n",
-      "rho_star = p_star/R/T_star;\n",
-      "\n",
-      "# from eq.(15.3)\n",
-      "mue_star = mue0*(T_star/T0)**1.5*(T0+110.)/(T_star+110.);\n",
-      "\n",
-      "# thus\n",
-      "Re_c_star = rho_star*ue*c/mue_star;\n",
-      "\n",
-      "# from eq.(18.22)\n",
-      "Cf_star = 1.328/sqrt(Re_c_star);\n",
-      "\n",
-      "# hence, the frictional drag on one surface of the plate is\n",
-      "D_f = 1./2.*rho_star*ue**2.*S*Cf_star;\n",
-      "\n",
-      "# thus, the total frictional drag is given by\n",
-      "D = 2.*D_f;\n",
-      "\n",
-      "print\"The total frictional drag is: D =\",D,\"N\""
-     ],
-     "language": "python",
-     "metadata": {},
-     "outputs": [
-      {
-       "output_type": "stream",
-       "stream": "stdout",
-       "text": [
-        "The total frictional drag is: D = 4978.09594496 N\n"
-       ]
-      }
-     ],
-     "prompt_number": 2
-    },
-    {
-     "cell_type": "heading",
-     "level": 2,
-     "metadata": {},
-     "source": [
-      "Example E03 : Pg 600"
-     ]
-    },
-    {
-     "cell_type": "code",
-     "collapsed": false,
-     "input": [
-      "# All the quantities are expressed in SI units\n",
-      "import math \n",
-      "from math import sqrt\n",
-      "Pr = 0.71;                    # Prandlt number of air at standard conditions\n",
-      "Pr_star = Pr;\n",
-      "Te = 288.;                     # temperature of the upper plate\n",
-      "ue = 1000.;                    # velocity of the upper plate\n",
-      "Me = 2.94;                    # Mach number of flow on the upper plate\n",
-      "p_star = 101000.;\n",
-      "R = 287.;                      # specific gas constant\n",
-      "gam = 1.4;                    # ratio of specific heats\n",
-      "T0 = 288.;                     # reference temperature at sea level\n",
-      "mue0 = 1.7894*10**-5;             # reference viscosity at sea level\n",
-      "c = 2.;                        # chord length of the plate\n",
-      "S = 40.;                       # plate planform area\n",
-      "\n",
-      "# recovery factor for a boundary layer is given by eq.(18.47) as\n",
-      "r = sqrt(Pr);\n",
-      "\n",
-      "# from ex.(8.2)\n",
-      "T_aw = Te*2.467;\n",
-      "T_w = T_aw;\n",
-      "\n",
-      "# from the Meador-Smart equation\n",
-      "T_star = Te*(0.45 + 0.55*T_w/Te + 0.16*r*(gam-1)/2*Me**2.);\n",
-      "\n",
-      "# from the equation of state\n",
-      "rho_star = p_star/R/T_star;\n",
-      "\n",
-      "# from eq.(15.3)\n",
-      "mue_star = mue0*(T_star/T0)**1.5*(T0+110)/(T_star+110.);\n",
-      "\n",
-      "# thus\n",
-      "Re_c_star = rho_star*ue*c/mue_star;\n",
-      "\n",
-      "# from eq.(18.22)\n",
-      "Cf_star = 1.328/sqrt(Re_c_star);\n",
-      "\n",
-      "# hence, the frictional drag on one surface of the plate is\n",
-      "D_f = 1./2.*rho_star*ue**2.*S*Cf_star;\n",
-      "\n",
-      "# thus, the total frictional drag is given by\n",
-      "D = 2.*D_f;\n",
-      "\n",
-      "print\"The total frictional drag is: D =\",D,\"N\""
-     ],
-     "language": "python",
-     "metadata": {},
-     "outputs": [
-      {
-       "output_type": "stream",
-       "stream": "stdout",
-       "text": [
-        "The total frictional drag is: D = 5014.11379241 N\n"
-       ]
-      }
-     ],
-     "prompt_number": 3
-    }
-   ],
-   "metadata": {}
-  }
- ]
-}
-\ No newline at end of file