Update documentation

Author: pkck28

.buildinfo

@@ -1,4 +1,4 @@
 # Sphinx build info version 1
 # This file hashes the configuration used when building these files. When it is not found, a full rebuild will be done.
-config: 6f562aacf0363db2e847aae4a00ecbb2
+config: 6c90a29069d49a417d620726cba51945
 tags: 645f666f9bcd5a90fca523b33c5a78b7

_images/conf.png

@@ -9,3 +9,10 @@ For the example airplane, following configuration is selected:
 * Wing mounted engines in tractor configuration
 * Conventional tail
 * Tricycle landing gear
+
+Below image shows this configuration in OpenVSP:
+
+<div style="width:80%; margin: auto;">
+
+![logos](images/conf.png)
+</div>

_images/wing_iso.png

@@ -0,0 +1,55 @@
+{
+ "cells": [
+  {
+   "cell_type": "markdown",
+   "id": "dd2e0801",
+   "metadata": {},
+   "source": [
+    "# Fuselage sizing\n",
+    "\n",
+    "This section talks about the initial sizing of fuselage and landing gear for the example airplane.\n",
+    "\n",
+    "## Fuselage \n",
+    "\n",
+    "lf_df = 7\n",
+    "lfc_df = 3\n",
+    "theta = 10 deg\n",
+    "structural depth of 1.5 in \n",
+    "cabin length\n",
+    "height\n",
+    "width\n",
+    "\n",
+    "Table 4.1\n",
+    "\n",
+    "Chapter 4 - Roskam 2\n",
+    "\n",
+    "Chapter 3 in Roskam Part 3\n",
+    "\n",
+    "Fig 3.1\n",
+    "\n",
+    "Fig 3.19\n",
+    "\n",
+    "Table 3.1\n",
+    "\n",
+    "Fig 3.51\n",
+    "\n",
+    "Section 3.5\n",
+    "\n",
+    "## Landing gear"
+   ]
+  }
+ ],
+ "metadata": {
+  "kernelspec": {
+   "display_name": "451",
+   "language": "python",
+   "name": "python3"
+  },
+  "language_info": {
+   "name": "python",
+   "version": "3.11.13"
+  }
+ },
+ "nbformat": 4,
+ "nbformat_minor": 5
+}

_sources/configuration.md

@@ -167,7 +167,14 @@
     "\n",
     "</div>\n",
     "\n",
-    "Based on the above table, the wing fuel capacity is 1770 lbs (computed using density of 100LL Avgas at low temperature) which is much higher than the [required fuel of 1060 lbs](initial_weight_estimation.ipynb#mtow-estimation). This concludes the wing planform sizing section. Note that many of these wing planform variables determine the aerodynamic efficiency and handling quality of the airplane, and hence, should be refined using carpet plots and/or numerical optimization in the later stages of design."
+    "Based on the above table, the wing fuel capacity is 1770 lbs (computed using density of 100LL Avgas at low temperature) which is much higher than the [required fuel of 1060 lbs](initial_weight_estimation.ipynb#mtow-estimation). Below image shows OpenVSP model of the wing:\n",
+    "\n",
+    "<div style=\"width:80%; margin: auto;\">\n",
+    "\n",
+    "![logos](images/wing_iso.png)\n",
+    "</div>\n",
+    "\n",
+    "This concludes the wing planform sizing section. Note that many of these wing planform variables determine the aerodynamic efficiency and handling quality of the airplane, and hence, should be refined using carpet plots and/or numerical optimization in the later stages of design."
    ]
   }
  ],

_sources/fuselage.ipynb

@@ -377,7 +377,10 @@ <h1>Aircraft Configuration<a class="headerlink" href="#aircraft-configuration" t
 <li><p>Conventional tail</p></li>
 <li><p>Tricycle landing gear</p></li>
 </ul>
-</section>
+<p>Below image shows this configuration in OpenVSP:</p>
+<div style="width:80%; margin: auto;">
+<p><img alt="logos" src="_images/conf.png" /></p>
+</div></section>
 
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