1 files changed, 16 insertions, 72 deletions
diff --git a/Engineering_Thermodynamics:_A_Computer_Approach_(SI_Units_Version)/ch16.ipynb b/Engineering_Thermodynamics:_A_Computer_Approach_(SI_Units_Version)/ch16.ipynb
index 32a42e59..8e3b0a97 100644
--- a/Engineering_Thermodynamics:_A_Computer_Approach_(SI_Units_Version)/ch16.ipynb
+++ b/Engineering_Thermodynamics:_A_Computer_Approach_(SI_Units_Version)/ch16.ipynb
@@ -1,6 +1,7 @@
 {
  "metadata": {
-  "name": ""
+  "name": "",
+  "signature": "sha256:9c7b64e157d08f3c7a366b1cf2d1f4de4a886f7dc2475d29ec96bb2b10e8dc31"
  },
  "nbformat": 3,
  "nbformat_minor": 0,
@@ -27,9 +28,7 @@
      "cell_type": "code",
      "collapsed": false,
      "input": [
-      "'''\n",
-      "Find the velocity of the gas \n",
-      "'''\n",
+      "\n",
       "\n",
       "import math \n",
       "\n",
@@ -74,9 +73,7 @@
      "cell_type": "code",
      "collapsed": false,
      "input": [
-      "'''\n",
-      "determine the pressure and the temperature \n",
-      "'''\n",
+      "\n",
       "\n",
       "# Variables\n",
       "p1 = 35.; \t\t\t#kN/m**2\n",
@@ -122,11 +119,7 @@
      "cell_type": "code",
      "collapsed": false,
      "input": [
-      "'''\n",
-      "Find the sonic velocity of -\n",
-      "(i) Crude oil \n",
-      "(ii) Mercury \n",
-      "'''\n",
+      "\n",
       "\n",
       "import math \n",
       "\n",
@@ -170,9 +163,7 @@
      "cell_type": "code",
      "collapsed": false,
      "input": [
-      "'''\n",
-      "Find the speed of the plane\n",
-      "'''\n",
+      "\n",
       "\n",
       "import math \n",
       "\n",
@@ -214,7 +205,7 @@
      "cell_type": "code",
      "collapsed": false,
      "input": [
-      "# Find the velocity of a bullet fired \n",
+      " \n",
       "\n",
       "# Variables\n",
       "a = 40*math.pi/180; \t\t\t#Mach angle in radians\n",
@@ -254,9 +245,6 @@
      "cell_type": "code",
      "collapsed": false,
      "input": [
-      "'''\n",
-      "find the velocity of the projectile. \n",
-      "'''\n",
       "\n",
       "import math \n",
       "\n",
@@ -299,9 +287,7 @@
      "cell_type": "code",
      "collapsed": false,
      "input": [
-      "'''\n",
-      "Determine the speed of the aircraft \n",
-      "'''\n",
+      "\n",
       "\n",
       "import math \n",
       "\n",
@@ -345,12 +331,6 @@
      "cell_type": "code",
      "collapsed": false,
      "input": [
-      "'''\n",
-      "Calculate-\n",
-      "(i) Stagnation pressure,\n",
-      "(ii) Stagnation temperature, and\n",
-      "(iii) Stagnation density.\n",
-      "'''\n",
       "\n",
       "import math \n",
       "\n",
@@ -401,10 +381,7 @@
      "cell_type": "code",
      "collapsed": false,
      "input": [
-      "'''\n",
-      "Compute stagnation properties and the local Mach number. \n",
-      "What would be the compressibility correction factor for a pitot-static tube \n",
-      "'''\n",
+      "\n",
       "\n",
       "import math \n",
       "\n",
@@ -465,11 +442,7 @@
      "cell_type": "code",
      "collapsed": false,
      "input": [
-      "'''\n",
-      "Calculate stagnation pressure if -\n",
-      "(i) Compressibility is neglected ;\n",
-      "(ii) Compressibility is accounted for.\n",
-      "'''\n",
+      "\n",
       "\n",
       "import math \n",
       "\n",
@@ -524,9 +497,7 @@
      "cell_type": "code",
      "collapsed": false,
      "input": [
-      "'''\n",
-      "Calculate the speed of the aircraft. \n",
-      "'''\n",
+      "\n",
       "\n",
       "import math \n",
       "\n",
@@ -570,9 +541,7 @@
      "cell_type": "code",
      "collapsed": false,
      "input": [
-      "'''\n",
-      "What is the true speed of the aircraft ?\n",
-      "'''\n",
+      "\n",
       "\n",
       "import math \n",
       "\n",
@@ -619,9 +588,6 @@
      "cell_type": "code",
      "collapsed": false,
      "input": [
-      "'''\n",
-      "Determine the reservoir pressure, temperature and the throat area.\n",
-      "'''\n",
       "\n",
       "import math \n",
       "\n",
@@ -670,9 +636,6 @@
      "cell_type": "code",
      "collapsed": false,
      "input": [
-      "'''\n",
-      "find the maximum flow rate of air.\n",
-      "'''\n",
       "\n",
       "import math \n",
       "\n",
@@ -717,9 +680,7 @@
      "cell_type": "code",
      "collapsed": false,
      "input": [
-      "'''\n",
-      "find the velocity of air flowing at the outlet of the nozzle.\n",
-      "'''\n",
+      "\n",
       "\n",
       "# Variables\n",
       "R = 287.; \t\t\t#J/kg K\n",
@@ -760,11 +721,7 @@
      "cell_type": "code",
      "collapsed": false,
      "input": [
-      "'''\n",
-      "find the mass rate of flow of air through the nozzle to the atmosphere when the pressure in the tank is-\n",
-      "(i) 140 kN/m 2 (abs.),\n",
-      "(ii) 300 kN/m 2\n",
-      "'''\n",
+      "\n",
       "\n",
       "import math \n",
       "\n",
@@ -825,13 +782,6 @@
      "cell_type": "code",
      "collapsed": false,
      "input": [
-      "'''\n",
-      "Determine-\n",
-      "(i) Stagnation temperature and stagnation pressure,\n",
-      "(ii) Sonic velocity and Mach number at this section,\n",
-      "(iii) Velocity, Mach number and flow area at outlet section where pressure is 110 kN/m 2 ,\n",
-      "(iv) Pressure, temperature, velocity and flow area at throat of the nozzle.\n",
-      "'''\n",
       "\n",
       "import math \n",
       "\n",
@@ -927,9 +877,7 @@
      "cell_type": "code",
      "collapsed": false,
      "input": [
-      "'''\n",
-      "determine the flow conditions before and after the shock wave.\n",
-      "'''\n",
+      "\n",
       "\n",
       "import math \n",
       "\n",
@@ -995,11 +943,7 @@
      "cell_type": "code",
      "collapsed": false,
      "input": [
-      "'''\n",
-      "Determine :\n",
-      "(i) Pressure, temperature and Mach number downstream of the shock, and\n",
-      "(ii) Strength of shock.\n",
-      "'''\n",
+      "\n",
       "\n",
       "import math \n",
       "\n",