{
 "cells": [
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "import manganite\n",
    "%load_ext manganite"
   ]
  },
  {
   "cell_type": "markdown",
   "metadata": {},
   "source": [
    "# Airfoil Analysis\n",
    "# with [AeroSandbox](https://github.com/peterdsharpe/AeroSandbox) and [Manganite](https://github.com/LCL-CAVE/manganite)\n",
    "\n",
    "## Description\n",
    "\n",
    "The Airfoil Design Demonstration Dashboard is a web-based showcase that provides a glimpse into the capabilities of airfoil analysis within a browser environment. It is built upon the open-source repository [AeroSandbox](https://github.com/peterdsharpe/Automotive-Airfoil-Design/) and serves as a demonstration of what's possible in the realm of virtual airfoil exploration.\n",
    "\n",
    "### Key Features\n",
    "\n",
    "1. **Geometry Visualization:** Explore an interactive airfoil geometry, pre-defined for demonstration purposes. Observe how changes in shape and size can impact aerodynamic behavior.\n",
    "\n",
    "2. **Simplified Angle of Attack:** Adjust the angle of attack within a limited range to see the immediate effects on lift and drag forces. \n",
    "\n",
    "3. **Kulfan Coordinates:** This demonstration employs Kulfan coordinates for the representation of airfoil shapes, providing insight into how airfoil data can be structured and analyzed.\n",
    "\n",
    "4. **Basic Constant Display:** View simplified constant values such as lift coefficient (CL), drag coefficient (CD), and moment coefficient (CM).\n",
    "\n",
    "5. **Visualization:** Visualize how changes in airfoil geometry and angle of attack influence aerodynamic characteristics."
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "import plotly.express as px\n",
    "import plotly.graph_objects as go\n",
    "import aerosandbox as asb\n",
    "import aerosandbox.numpy as np\n",
    "import copy\n",
    "import plotly.figure_factory as ff\n",
    "import pandas as pd"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "%%mnn widget --type slider -20:20:0.1 --tab \"Operating Conditions\" --header \"Angle of Attack\" --var alpha\n",
    "alpha = 8.7"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "streamline_density = 1\n",
    "height = 0\n",
    "ground_effect = False"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "%%mnn widget --type slider -0.1:0.7:0.01 --tab \"Shape Parameters\" --header \"Upper surface 1\" --var upper_1 --position 0 0 2\n",
    "upper_1 = 0.25"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "%%mnn widget --type slider -0.1:0.7:0.01 --tab \"Shape Parameters\" --header \"Upper surface 2\" --var upper_2 --position 0 2 2\n",
    "upper_2 = 0.47"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "%%mnn widget --type slider -0.1:0.7:0.01 --tab \"Shape Parameters\" --header \"Upper surface 3\" --var upper_3 --position 0 4 2\n",
    "upper_3 = 0.024"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "%%mnn widget --type slider -0.5:0.3:0.01 --tab \"Shape Parameters\" --header \"Lower surface 1\" --var lower_1 --position 1 0 2\n",
    "lower_1 = -0.11"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "%%mnn widget --type slider 0:0.7:0.01 --tab \"Shape Parameters\" --header \"Lower surface 2\" --var lower_2 --position 1 2 2\n",
    "lower_2 = 0.06"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "%%mnn widget --type slider 0:0.7:0.01 --tab \"Shape Parameters\" --header \"Lower surface 3\" --var lower_3 --position 1 4 2\n",
    "lower_3 = -0.06"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "def display_graph(n_clicks, alpha, height, streamline_density, kulfan_upper, kulfan_lower, analyze_button_pressed = False):\n",
    "\n",
    "    ### Start constructing the figure\n",
    "    airfoil = asb.Airfoil(\n",
    "        coordinates=asb.get_kulfan_coordinates(\n",
    "            lower_weights=np.array(lower_values),\n",
    "            upper_weights=np.array(upper_values),\n",
    "            TE_thickness=0,\n",
    "            enforce_continuous_LE_radius=False,\n",
    "            n_points_per_side=200\n",
    "        )\n",
    "    )\n",
    "\n",
    "    # ### Do coordinates output\n",
    "    # coordinates_output = \"\\n\".join(\n",
    "    #     [\"```\"] +\n",
    "    #     [\"AeroSandbox Airfoil\"] +\n",
    "    #     [\"\\t%f\\t%f\" % tuple(coordinate) for coordinate in airfoil.coordinates] +\n",
    "    #     [\"```\"]\n",
    "    # )\n",
    "\n",
    "    ### Continue doing the airfoil things\n",
    "    airfoil = airfoil.rotate(angle=-np.radians(alpha))\n",
    "    airfoil = airfoil.translate(\n",
    "        0,\n",
    "        height + 0.5 * np.sind(alpha)\n",
    "    )\n",
    "    fig = go.Figure()\n",
    "    fig.add_trace(\n",
    "        go.Scatter(\n",
    "            x=airfoil.x(),\n",
    "            y=airfoil.y(),\n",
    "            mode=\"lines\",\n",
    "            name=\"Airfoil\",\n",
    "            fill=\"toself\",\n",
    "            line=dict(\n",
    "                color=\"blue\"\n",
    "            )\n",
    "        )\n",
    "    )\n",
    "\n",
    "    ### Default text output\n",
    "    text_output = 'Click \"Analyze\" to compute aerodynamics!'\n",
    "    output = text_output\n",
    "\n",
    "    xrng = (-0.5, 1.5)\n",
    "    yrng = (-0.6, 0.6) if not ground_effect else (0, 1.2)\n",
    "\n",
    "    if analyze_button_pressed:\n",
    "\n",
    "        analysis = asb.AirfoilInviscid(\n",
    "            airfoil=airfoil.repanel(50),\n",
    "            op_point=asb.OperatingPoint(\n",
    "                velocity=1,\n",
    "                alpha=0,\n",
    "            ),\n",
    "            ground_effect=ground_effect\n",
    "        )\n",
    "\n",
    "        x = np.linspace(*xrng, 100)\n",
    "        y = np.linspace(*yrng, 100)\n",
    "        X, Y = np.meshgrid(x, y)\n",
    "        u, v = analysis.calculate_velocity(\n",
    "            x_field=X.flatten(),\n",
    "            y_field=Y.flatten()\n",
    "        )\n",
    "        U = u.reshape(X.shape)\n",
    "        V = v.reshape(Y.shape)\n",
    "\n",
    "        streamline_fig = ff.create_streamline(\n",
    "            x, y, U, V,\n",
    "            arrow_scale=1e-16,\n",
    "            density=streamline_density,\n",
    "            line=dict(\n",
    "                color=\"#ff82a3\"\n",
    "            ),\n",
    "            name=\"Streamlines\"\n",
    "        )\n",
    "\n",
    "        fig = go.Figure(\n",
    "            data=streamline_fig.data + fig.data\n",
    "        )\n",
    "\n",
    "        output = pd.DataFrame(\n",
    "            {\n",
    "                \"Engineering Quantity\": [\n",
    "                    \"C_L\"\n",
    "                ],\n",
    "                \"Value\"               : [\n",
    "                    f\"{analysis.Cl:.3f}\"\n",
    "                ]\n",
    "            }\n",
    "        )\n",
    "\n",
    "    fig.update_layout(\n",
    "        xaxis_title=\"x/c\",\n",
    "        yaxis_title=\"y/c\",\n",
    "        showlegend=False,\n",
    "        yaxis=dict(scaleanchor=\"x\", scaleratio=1),\n",
    "        margin={'t': 0},\n",
    "        title=None,\n",
    "    )\n",
    "\n",
    "    fig.update_xaxes(range=xrng)\n",
    "    fig.update_yaxes(range=yrng)\n",
    "\n",
    "    return fig, output"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "%%mnn widget --type plot --var aero_fig --tab \"Shape Parameters\" --header \"Airfoil Cross section\" --position 2 0 6\n",
    "upper_values = [upper_1, upper_2,upper_3]\n",
    "lower_values = [lower_1, lower_2, lower_3]\n",
    "aero_fig, text_output = display_graph(1,alpha=alpha,height=0,streamline_density=streamline_density, kulfan_upper=upper_values, kulfan_lower=lower_values)\n"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "%%mnn execute --on button \"Analyze\" --returns aero_performance\n",
    "\n",
    "aero_fig_lines, aero_performance = display_graph(1,alpha=alpha,height=0,streamline_density=streamline_density, kulfan_upper=upper_values, kulfan_lower=lower_values, analyze_button_pressed = True)\n"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "%%mnn widget --type plot --var aero_fig_lines --tab \"Aerodynamic Performance\" --header \"Streamlines\" --position 0 0 6\n",
    "\n",
    "simu_ready = aero_performance\n",
    "aero_fig_lines\n"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "%%mnn widget --type table --tab \"Aerodynamic Performance\" --position 1 2 4 --header \"Metrics\" --var performance_values\n",
    "\n",
    "performance_values = aero_performance"
   ]
  }
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