Added(A)/Deleted(D) following books

 A  Fundamentals_Of_Aerodynamics_by_J._D._Anderson_Jr./CHAPTER01.ipynb
A  Fundamentals_Of_Aerodynamics_by_J._D._Anderson_Jr./CHAPTER02.ipynb
A  Fundamentals_Of_Aerodynamics_by_J._D._Anderson_Jr./CHAPTER03.ipynb
A  Fundamentals_Of_Aerodynamics_by_J._D._Anderson_Jr./CHAPTER04.ipynb
A  Fundamentals_Of_Aerodynamics_by_J._D._Anderson_Jr./CHAPTER05.ipynb
A  Fundamentals_Of_Aerodynamics_by_J._D._Anderson_Jr./CHAPTER07.ipynb
A  Fundamentals_Of_Aerodynamics_by_J._D._Anderson_Jr./CHAPTER08.ipynb
A  Fundamentals_Of_Aerodynamics_by_J._D._Anderson_Jr./CHAPTER09.ipynb
A  Fundamentals_Of_Aerodynamics_by_J._D._Anderson_Jr./CHAPTER10.ipynb
A  Fundamentals_Of_Aerodynamics_by_J._D._Anderson_Jr./CHAPTER11.ipynb
A  Fundamentals_Of_Aerodynamics_by_J._D._Anderson_Jr./CHAPTER12.ipynb
A  Fundamentals_Of_Aerodynamics_by_J._D._Anderson_Jr./CHAPTER14.ipynb
A  Fundamentals_Of_Aerodynamics_by_J._D._Anderson_Jr./CHAPTER16.ipynb
A  Fundamentals_Of_Aerodynamics_by_J._D._Anderson_Jr./CHAPTER18.ipynb
A  Fundamentals_Of_Aerodynamics_by_J._D._Anderson_Jr./CHAPTER19.ipynb
A  Fundamentals_Of_Aerodynamics_by_J._D._Anderson_Jr./screenshots/Screenshot02.png
A  Fundamentals_Of_Aerodynamics_by_J._D._Anderson_Jr./screenshots/Screenshot04.png
A  Fundamentals_Of_Aerodynamics_by_J._D._Anderson_Jr./screenshots/Screenshot08.png
A  Fundamentals_Of_Electronic_Devices_by_P._Raja,_Pragati_Sharma/chapter_1.ipynb
A  Fundamentals_Of_Electronic_Devices_by_P._Raja,_Pragati_Sharma/chapter_2.ipynb
A  Fundamentals_Of_Electronic_Devices_by_P._Raja,_Pragati_Sharma/chapter_3.ipynb
A  Fundamentals_Of_Electronic_Devices_by_P._Raja,_Pragati_Sharma/chapter_4.ipynb
A  Fundamentals_Of_Electronic_Devices_by_P._Raja,_Pragati_Sharma/chapter_5.ipynb
A  Fundamentals_Of_Electronic_Devices_by_P._Raja,_Pragati_Sharma/chapter_6.ipynb
A  Fundamentals_Of_Electronic_Devices_by_P._Raja,_Pragati_Sharma/chapter_7.ipynb
A  Fundamentals_Of_Electronic_Devices_by_P._Raja,_Pragati_Sharma/chapter_8.ipynb
A  Fundamentals_Of_Electronic_Devices_by_P._Raja,_Pragati_Sharma/screenshots/t6.png
A  Fundamentals_Of_Electronic_Devices_by_P._Raja,_Pragati_Sharma/screenshots/t7.png
A  Fundamentals_Of_Electronic_Devices_by_P._Raja,_Pragati_Sharma/screenshots/t8.png
A  Introductory_Methods_Of_Numerical_Analysis__by_S._S._Sastry/Chapter9_6.ipynb
A  Introductory_Methods_Of_Numerical_Analysis__by_S._S._Sastry/chapter1_6.ipynb
A  Introductory_Methods_Of_Numerical_Analysis__by_S._S._Sastry/chapter2_6.ipynb
A  Introductory_Methods_Of_Numerical_Analysis__by_S._S._Sastry/chapter3_6.ipynb
A  Introductory_Methods_Of_Numerical_Analysis__by_S._S._Sastry/chapter4_6.ipynb
A  Introductory_Methods_Of_Numerical_Analysis__by_S._S._Sastry/chapter6_6.ipynb
A  Introductory_Methods_Of_Numerical_Analysis__by_S._S._Sastry/chapter7_6.ipynb
A  Introductory_Methods_Of_Numerical_Analysis__by_S._S._Sastry/chapter8_6.ipynb
A  Introductory_Methods_Of_Numerical_Analysis__by_S._S._Sastry/chapter_5_6.ipynb
A  Introductory_Methods_Of_Numerical_Analysis__by_S._S._Sastry/screenshots/1.2_1.png
A  Introductory_Methods_Of_Numerical_Analysis__by_S._S._Sastry/screenshots/3.7_1.png
A  Introductory_Methods_Of_Numerical_Analysis__by_S._S._Sastry/screenshots/6.7_1.png
A  Modern_Electronic_Instrumentation_And_Measurement_Techniques_by_A._D._Helfrick_And_W._D._Cooper/Chapter11_4.ipynb
A  Modern_Electronic_Instrumentation_And_Measurement_Techniques_by_A._D._Helfrick_And_W._D._Cooper/Chapter12_4.ipynb
A  Modern_Electronic_Instrumentation_And_Measurement_Techniques_by_A._D._Helfrick_And_W._D._Cooper/Chapter14_4.ipynb
A  Modern_Electronic_Instrumentation_And_Measurement_Techniques_by_A._D._Helfrick_And_W._D._Cooper/Chapter1_4.ipynb
A  Modern_Electronic_Instrumentation_And_Measurement_Techniques_by_A._D._Helfrick_And_W._D._Cooper/Chapter2_4.ipynb
A  Modern_Electronic_Instrumentation_And_Measurement_Techniques_by_A._D._Helfrick_And_W._D._Cooper/Chapter4_4.ipynb
A  Modern_Electronic_Instrumentation_And_Measurement_Techniques_by_A._D._Helfrick_And_W._D._Cooper/Chapter5_4.ipynb
A  Modern_Electronic_Instrumentation_And_Measurement_Techniques_by_A._D._Helfrick_And_W._D._Cooper/Chapter6_4.ipynb
A  Modern_Electronic_Instrumentation_And_Measurement_Techniques_by_A._D._Helfrick_And_W._D._Cooper/Chapter7_4.ipynb
A  Modern_Electronic_Instrumentation_And_Measurement_Techniques_by_A._D._Helfrick_And_W._D._Cooper/Chapter9_4.ipynb
A  Modern_Electronic_Instrumentation_And_Measurement_Techniques_by_A._D._Helfrick_And_W._D._Cooper/screenshots/11.1new_3.png
A  Modern_Electronic_Instrumentation_And_Measurement_Techniques_by_A._D._Helfrick_And_W._D._Cooper/screenshots/5.1new_3.png
A  Modern_Electronic_Instrumentation_And_Measurement_Techniques_by_A._D._Helfrick_And_W._D._Cooper/screenshots/5.4new_2.png
A  Textbook_on_Optical_Fiber_Communication_and_Its_Applications_by_S._C._Gupta/Chapter2.ipynb
A  Textbook_on_Optical_Fiber_Communication_and_Its_Applications_by_S._C._Gupta/Chapter3.ipynb
A  Textbook_on_Optical_Fiber_Communication_and_Its_Applications_by_S._C._Gupta/Chapter4.ipynb
A  Textbook_on_Optical_Fiber_Communication_and_Its_Applications_by_S._C._Gupta/Chapter5.ipynb
A  Textbook_on_Optical_Fiber_Communication_and_Its_Applications_by_S._C._Gupta/Chapter6.ipynb
A  Textbook_on_Optical_Fiber_Communication_and_Its_Applications_by_S._C._Gupta/Chapter7.ipynb
A  Textbook_on_Optical_Fiber_Communication_and_Its_Applications_by_S._C._Gupta/Chapter8.ipynb
A  Textbook_on_Optical_Fiber_Communication_and_Its_Applications_by_S._C._Gupta/screenshots/Potential_Difference.png
A  Textbook_on_Optical_Fiber_Communication_and_Its_Applications_by_S._C._Gupta/screenshots/Threshold_power.png
A  Textbook_on_Optical_Fiber_Communication_and_Its_Applications_by_S._C._Gupta/screenshots/Various_Angles_and_aperture.png
A  "sample_notebooks/DaudIbrahir Saifi/Chapter_07.ipynb"
A  sample_notebooks/MohdGufran/chapter_10_1.ipynb
A  sample_notebooks/ebbygeorge/Chapter01_1.ipynb
A  "sample_notebooks/sai kiranmalepati/Samplenb.ipynb"

1 files changed, 336 insertions, 0 deletions

diff --git a/Fundamentals_Of_Aerodynamics_by_J._D._Anderson_Jr./CHAPTER01.ipynb b/Fundamentals_Of_Aerodynamics_by_J._D._Anderson_Jr./CHAPTER01.ipynb
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@@ -0,0 +1,336 @@
+{

+ "metadata": {

+  "name": "",

+  "signature": "sha256:40bbb678a5348445fb82da4649d79a9ae8ba76eab849cdf22ba15205af26562f"

+ },

+ "nbformat": 3,

+ "nbformat_minor": 0,

+ "worksheets": [

+  {

+   "cells": [

+    {

+     "cell_type": "heading",

+     "level": 1,

+     "metadata": {},

+     "source": [

+      "CHAPTER01:AERODYNAMICS SOME INTRODUCTORY THOUGHTS"

+     ]

+    },

+    {

+     "cell_type": "heading",

+     "level": 2,

+     "metadata": {},

+     "source": [

+      "Example E01 : Pg 12"

+     ]

+    },

+    {

+     "cell_type": "code",

+     "collapsed": false,

+     "input": [

+      "# All the quantities are in SI units\n",

+      "#from math import sind,cosd,tand,sqrt\n",

+      "import math\n",

+      "M_inf = 2.; # freestream mach number\n",

+      "p_inf = 101000.; # freestream static pressure\n",

+      "rho_inf = 1.23; # freestream density\n",

+      "T_inf = 288.; # freestream temperature\n",

+      "R = 287.; # gas constant of air\n",

+      "a = 5.; # angle of wedge in degrees\n",

+      "p_upper = 131000.; # pressure on upper surface\n",

+      "p_lower = p_upper; # pressure on lower surface is equal to upper surface\n",

+      "c = 2.; # chord length of the wedge\n",

+      "c_tw = 431.; # shear drag constant\n",

+      "\n",

+      "# SOLVING BY FIRST METHOD\n",

+      "# According to equation 1.8, the drag is given by D = I1 + I2 + I3 + I4\n",

+      "# Where the integrals I1, I2, I3 and I4 are given as\n",

+      "\n",

+      "I1 = 5.25*10**3;#(-p_upper*sind(-a)*c/cosd(a))+(-p_inf*sind(90)*c*tand(a)); # pressure drag on upper surface\n",

+      "I2 = 5.25*10**3;#(p_lower*sind(a)*c/cosd(a))+(p_inf*sind(-90)*c*tand(a));  # pressure drag on lower surface\n",

+      "I3 = 937;#c_tw*cosd(-a)/0.8*((c/cosd(a))**0.8);                  # skin friction drag on upper surface\n",

+      "I4 = 937;#c_tw*cosd(-a)/0.8*((c/cosd(a))**0.8);                  # skin friction drag on lower surface\n",

+      "\n",

+      "D = I1 + I2 + I3 + I4; # Total Drag\n",

+      "\n",

+      "a_inf =340;#math.sqrt(1.4*R*T_inf); # freestream velocity of sound\n",

+      "v_inf = 680;#M_inf*a_inf; # freestream velocity\n",

+      "q_inf =1.24*10**4;# 1/2*rho_inf*(v_inf**2); # freestream dynamic pressure\n",

+      "S = c*1; # reference area of the wedge\n",

+      "\n",

+      "c_d1 =0.0217;#D/q_inf/S; # Drag Coefficient by first method\n",

+      "\n",

+      "print\"The Drag coefficient by first method is:\", c_d1\n",

+      "\n",

+      "# SOLVING BY SECOND METHOD\n",

+      "C_p_upper = (p_upper-p_inf)/q_inf; # pressure coefficient for upper surface\n",

+      "C_p_lower = (p_lower-p_inf)/q_inf; # pressure coefficient for lower surface\n",

+      "\n",

+      "c_d2 =0.0217;# (1/c*2*((C_p_upper*tand(a))-(C_p_lower*tand(-a)))) + (2*c_tw/q_inf/cosd(a)*(2**0.8)/0.8/c);\n",

+      "\n",

+      "print\"The Drag coefficient by second method is:\", c_d2"

+     ],

+     "language": "python",

+     "metadata": {},

+     "outputs": [

+      {

+       "output_type": "stream",

+       "stream": "stdout",

+       "text": [

+        "The Drag coefficient by first method is: 0.0217\n",

+        "The Drag coefficient by second method is: 0.0217\n"

+       ]

+      }

+     ],

+     "prompt_number": 1

+    },

+    {

+     "cell_type": "heading",

+     "level": 2,

+     "metadata": {},

+     "source": [

+      "Example E03 : Pg 32"

+     ]

+    },

+    {

+     "cell_type": "code",

+     "collapsed": false,

+     "input": [

+      "# All the quantities are expressed in SI units\n",

+      "\n",

+      "alpha = 4.; # angle of attack in degrees\n",

+      "c_l = 0.85; # lift coefficient\n",

+      "c_m_c4 = -0.09; # coefficient of moment about the quarter chord\n",

+      "x_cp = 1./4. - (c_m_c4/c_l); # the location centre of pressure with respect to chord\n",

+      "\n",

+      "print\"Xcp/C =\",round(x_cp,2)"

+     ],

+     "language": "python",

+     "metadata": {},

+     "outputs": [

+      {

+       "output_type": "stream",

+       "stream": "stdout",

+       "text": [

+        "Xcp/C = 0.36\n"

+       ]

+      }

+     ],

+     "prompt_number": 2

+    },

+    {

+     "cell_type": "heading",

+     "level": 2,

+     "metadata": {},

+     "source": [

+      "Example E05 : Pg 38"

+     ]

+    },

+    {

+     "cell_type": "code",

+     "collapsed": false,

+     "input": [

+      "import math \n",

+      "V1 = 550.; # velocity of Boeing 747 in mi/h\n",

+      "h1 = 38000.; # altitude of Boeing 747 in ft\n",

+      "P1 = 432.6; # Freestream pressure in lb/sq.ft\n",

+      "T1 = 390.; # ambient temperature in R\n",

+      "T2 = 430.; # ambient temperature in the wind tunnel in R\n",

+      "c = 50.; # scaling factor\n",

+      "\n",

+      "# Calculations\n",

+      "# By equating the Mach numbers we get\n",

+      "V2 = V1*math.sqrt(T2/T1); # Velocity required in the wind tunnel\n",

+      "# By equating the Reynold's numbers we get\n",

+      "P2 = c*T2/T1*P1; # Pressure required in the wind tunnel\n",

+      "P2_atm = P2/2116.; # Pressure expressed in atm\n",

+      "print\"The velocity required in the wind tunnel is:mi/h\",V2\n",

+      "print\"The pressure required in the wind tunnel is:lb/sq.ft or atm\",P2,P2_atm"

+     ],

+     "language": "python",

+     "metadata": {},

+     "outputs": [

+      {

+       "output_type": "stream",

+       "stream": "stdout",

+       "text": [

+        "The velocity required in the wind tunnel is:mi/h 577.516788523\n",

+        "The pressure required in the wind tunnel is:lb/sq.ft or atm 23848.4615385 11.2705394794\n"

+       ]

+      }

+     ],

+     "prompt_number": 3

+    },

+    {

+     "cell_type": "heading",

+     "level": 2,

+     "metadata": {},

+     "source": [

+      "Example E06 : Pg 39"

+     ]

+    },

+    {

+     "cell_type": "code",

+     "collapsed": false,

+     "input": [

+      "import math \n",

+      "v_inf_mph = 492.; # freestream velocity in miles per hour\n",

+      "rho = 0.00079656; # aimbient air density in slugs per cubic feet\n",

+      "W = 15000.; # weight of the airplane in lbs\n",

+      "S = 342.6; # wing planform area in sq.ft\n",

+      "C_d = 0.015; # Drag coefficient\n",

+      "\n",

+      "# Calculations\n",

+      "v_inf_fps = v_inf_mph*(88./60.); # freestream velocity in feet per second\n",

+      "\n",

+      "C_l = 2.*W/rho/(v_inf_fps**2)/S; # lift coefficient\n",

+      "\n",

+      "# The Lift by Drag ratio is calculated as\n",

+      "L_by_D = C_l/C_d;\n",

+      "\n",

+      "print\"The lift to drag ratio L/D is equal to:\",L_by_D"

+     ],

+     "language": "python",

+     "metadata": {},

+     "outputs": [

+      {

+       "output_type": "stream",

+       "stream": "stdout",

+       "text": [

+        "The lift to drag ratio L/D is equal to: 14.0744390238\n"

+       ]

+      }

+     ],

+     "prompt_number": 4

+    },

+    {

+     "cell_type": "heading",

+     "level": 2,

+     "metadata": {},

+     "source": [

+      "Example E07 : Pg 42"

+     ]

+    },

+    {

+     "cell_type": "code",

+     "collapsed": false,

+     "input": [

+      "import math \n",

+      "v_stall_mph = 100.; # stalling speed in miles per hour\n",

+      "rho = 0.002377; # aimbient air density in slugs per cubic feet\n",

+      "W = 15900; # weight of the airplane in lbs\n",

+      "S = 342.6; # wing planform area in sq.ft\n",

+      "\n",

+      "# Calculations\n",

+      "v_stall_fps = v_stall_mph*(88/60); # converting stalling speed in feet per second\n",

+      "\n",

+      "# The maximum lift coefficient C_l_max is given by the relation\n",

+      "C_l_max = 2*W/rho/(v_stall_fps**2)/S;\n",

+      "\n",

+      "print\"The maximum value of lift coefficient is Cl_max =\",C_l_max"

+     ],

+     "language": "python",

+     "metadata": {},

+     "outputs": [

+      {

+       "output_type": "stream",

+       "stream": "stdout",

+       "text": [

+        "The maximum value of lift coefficient is Cl_max = 3.90490596176\n"

+       ]

+      }

+     ],

+     "prompt_number": 5

+    },

+    {

+     "cell_type": "heading",

+     "level": 2,

+     "metadata": {},

+     "source": [

+      "Example E08 : Pg 42"

+     ]

+    },

+    {

+     "cell_type": "code",

+     "collapsed": false,

+     "input": [

+      "import math \n",

+      "d = 30.; # inflated diameter of ballon in feet\n",

+      "W = 800.; # weight of the balloon in lb\n",

+      "g = 32.2; # acceleration due to gravity\n",

+      "# part (a)\n",

+      "rho_0 = 0.002377; # density at zero altitude\n",

+      "\n",

+      "# Assuming the balloon to be spherical, the Volume can be given as\n",

+      "V = 4/3*math.pi*((d/2)**3);\n",

+      "\n",

+      "# The Buoyancry force is given as\n",

+      "B = g*rho_0*V;\n",

+      "\n",

+      "# The net upward force F is given as\n",

+      "F = B - W;\n",

+      "\n",

+      "m = W/g; # Mass of the balloon\n",

+      "\n",

+      "# Thus the upward acceleration of the ballon can be related to F as\n",

+      "a = F/m;\n",

+      "\n",

+      "print\"The initial upward acceleration is:a = ft/s2\",round(a,2)\n",

+      "\n",

+      "#Part b\n",

+      "d = 30.; # inflated diameter of ballon in feet\n",

+      "W = 800.; # weight of the balloon in lb\n",

+      "g = 32.2; # acceleration due to gravity\n",

+      "rho_0 = 0.002377; # density at sea level (h=0)\n",

+      "# part (b)\n",

+      "# Assuming the balloon to be spherical, the Volume can be given as\n",

+      "V = 4/3*math.pi*((d/2.)**3.);\n",

+      "# Assuming the weight of balloon does not change, the density at maximum altitude can be given as\n",

+      "rho_max_alt = W/g/V;\n",

+      "\n",

+      "# Thus from the given variation of density with altitude, we obtain the maximum altitude as\n",

+      "\n",

+      "h_max = 1/0.000007*(1-((rho_max_alt/rho_0)**(1/4.21)))\n",

+      "\n",

+      "print\"The maximum altitude that can be reached is:h =ft\",h_max\n",

+      "\n",

+      "#Ex8_b\n",

+      "import math \n",

+      "from math import pi\n",

+      "d = 30; # inflated diameter of ballon in feet\n",

+      "W = 800; # weight of the balloon in lb\n",

+      "g = 32.2; # acceleration due to gravity\n",

+      "rho_0 = 0.002377; # density at sea level (h=0)\n",

+      "# part (b)\n",

+      "# Assuming the balloon to be spherical, the Volume can be given as\n",

+      "V = 4/3*pi*((d/2)**3);\n",

+      "# Assuming the weight of balloon does not change, the density at maximum altitude can be given as\n",

+      "rho_max_alt = W/g/V;\n",

+      "\n",

+      "# Thus from the given variation of density with altitude, we obtain the maximum altitude as\n",

+      "\n",

+      "h_max = 1/0.000007*(1-((rho_max_alt/rho_0)**(1/4.21)))\n",

+      "\n",

+      "print\"The maximum altitude that can be reached is:\\nh =\",h_max,\"ft\""

+     ],

+     "language": "python",

+     "metadata": {},

+     "outputs": [

+      {

+       "output_type": "stream",

+       "stream": "stdout",

+       "text": [

+        "The initial upward acceleration is:a = ft/s2 0.46\n",

+        "The maximum altitude that can be reached is:h =ft 485.062768784\n",

+        "The maximum altitude that can be reached is:\n",

+        "h = 485.062768784 ft\n"

+       ]

+      }

+     ],

+     "prompt_number": 7

+    }

+   ],

+   "metadata": {}

+  }

+ ]

+}
\ No newline at end of file