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   "source": [
    "# CHAPTER11:SUBSONIC COMPRESSIBLE FLOW OVER AIRFOILS LINEAR THEOREY"
   ]
  },
  {
   "cell_type": "markdown",
   "metadata": {},
   "source": [
    "## Example E01 : Pg 382"
   ]
  },
  {
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   "execution_count": 1,
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   "outputs": [
    {
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     "text": [
      "(a)The Cp after compressibility corrections is: -0.375 Cp\n"
     ]
    }
   ],
   "source": [
    "# All the quantities are expressed in SI units\n",
    "import math \n",
    "Cp_incompressible = -0.3;                    # Cp for incompressible flow\n",
    "M = 0.6;                                     # Mach number\n",
    "# Thus from eq.(11.52)\n",
    "Cp_compressible = Cp_incompressible/math.sqrt(1-M**2);\n",
    "print\"(a)The Cp after compressibility corrections is:\",Cp_compressible,\"Cp\""
   ]
  },
  {
   "cell_type": "markdown",
   "metadata": {},
   "source": [
    "## Example E02 : Pg 383"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": 1,
   "metadata": {
    "collapsed": false
   },
   "outputs": [
    {
     "name": "stdout",
     "output_type": "stream",
     "text": [
      "(a)The cl after compressibility corrections is: cl = 8.7982192499 alpha\n"
     ]
    }
   ],
   "source": [
    "# All the quantities are expressed in SI units\n",
    "import math \n",
    "cl_incompressible = 2*math.pi;                    # lift curve slope\n",
    "M_inf = 0.7;                                  # Mach number\n",
    "# from eq.(11.52)\n",
    "cl_compressible = cl_incompressible/math.sqrt(1-M_inf**2);        # compressible lift curve slope\n",
    "print\"(a)The cl after compressibility corrections is: cl =\",cl_compressible,\"alpha\""
   ]
  }
 ],
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