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  {
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   "source": [
    "# Plane Landing Example\n",
    "\n",
    "This example demonstrates how to use flight-mech to compute the landing characteristics of a plane."
   ]
  },
  {
   "cell_type": "markdown",
   "metadata": {},
   "source": [
    "## Imports"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": 1,
   "metadata": {},
   "outputs": [],
   "source": [
    "# Python imports\n",
    "import os\n",
    "import sys\n",
    "sys.path.append(\"..\")\n",
    "\n",
    "# Additional imports\n",
    "import numpy as np\n",
    "import matplotlib.pyplot as plt\n",
    "\n",
    "# Flight-Mech imports\n",
    "from flight_mech.plane import Plane"
   ]
  },
  {
   "cell_type": "markdown",
   "metadata": {},
   "source": [
    "## Plane definition\n",
    "\n",
    "Let us use in this case the Cessna Citation III defined in the database."
   ]
  },
  {
   "cell_type": "code",
   "execution_count": 2,
   "metadata": {},
   "outputs": [],
   "source": [
    "# Load the plane\n",
    "plane = Plane(\"cessna_citation_III\")"
   ]
  },
  {
   "cell_type": "markdown",
   "metadata": {},
   "source": [
    "## Landing characteristics\n",
    "\n",
    "We can now define a runway by its altitude and friction coefficient, set the plane in landing configuration and compute the landing distance and velocities."
   ]
  },
  {
   "cell_type": "code",
   "execution_count": 3,
   "metadata": {},
   "outputs": [
    {
     "name": "stdout",
     "output_type": "stream",
     "text": [
      "weight [N] 54936.0\n",
      "landing speed [m.s-1] 45.33584221198617\n",
      "landing distance [m] 976.4188122310702\n"
     ]
    }
   ],
   "source": [
    "# Define the friction coefficient of the landing strip\n",
    "mu = 0.1\n",
    "\n",
    "# Define the landing altitude\n",
    "z = 0\n",
    "\n",
    "# Update some coefficients to set the landing configuration\n",
    "plane.C_D_0 = plane.C_D_0 * 1.1\n",
    "plane.m_fuel = 0\n",
    "plane.C_L_max = 2.5\n",
    "plane.update_variables(force=True)\n",
    "\n",
    "# Print the results\n",
    "print(\"weight [N]\", plane.P)\n",
    "print(\"landing speed [m.s-1]\", plane.compute_landing_speed(z))\n",
    "print(\"landing distance [m]\", plane.compute_landing_distance(z, mu, C_L=0))"
   ]
  }
 ],
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