{
 "cells": [
  {
   "cell_type": "markdown",
   "metadata": {},
   "source": [
    "# Postprocessing for DU00-W-212: Coefficients of lift and drag\n",
    "## Angle of attack sweep"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "import yaml\n",
    "import matplotlib.pyplot as plt\n",
    "import numpy as np"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "size=14\n",
    "params = {'legend.fontsize': 'large',\n",
    "          'axes.labelsize': size,\n",
    "          'axes.titlesize': size,\n",
    "          'xtick.labelsize': size,\n",
    "          'ytick.labelsize': size}\n",
    "plt.rcParams.update(params)"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "# For website workflow\n",
    "path_prefix = '../../nalu-wind/2D_airfoil_Transition/DU00-W-212/figures_and_scripts/'"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "re_list=[3]\n",
    "\n",
    "n_re=len(re_list)\n",
    "\n",
    "for i in range(n_re):\n",
    "    re   = re_list[i]\n",
    "    file =path_prefix+'../reference_data/exp_du00w212_re{:02d}M.yaml'.format(int(re))\n",
    "    with open(file, \"r\") as data:\n",
    "        clcd=yaml.safe_load(data)\n",
    "\n",
    "    with open(path_prefix+'../performance/du00w212_F_rey{:08d}.yaml'.format(int(re*1e6)), \"r\") as data3:\n",
    "        cfd_trans=yaml.safe_load(data3)\n",
    "\n",
    "    with open(path_prefix+'../performance/du00w212_F_rey{:08d}_turb.yaml'.format(int(re*1e6)), \"r\") as data1:\n",
    "        cfd_turb=yaml.safe_load(data1)\n",
    "\n",
    "\n",
    "    plt.figure(figsize=(11,4))\n",
    "    plt.subplot(1, 3, 1)\n",
    "    plt.plot(clcd['DU00W212']['aoa'],clcd['DU00W212']['cl'],'ko')\n",
    "    plt.plot(cfd_turb['du00w212_F']['aoa'],cfd_turb['du00w212_F']['cl'],'--')\n",
    "    plt.plot(cfd_trans['du00w212_F']['aoa'],cfd_trans['du00w212_F']['cl'])\n",
    "    plt.xlabel('Angle of Attack [deg]')\n",
    "    plt.xlim([-10, 20])\n",
    "    plt.ylim([-1, 2])\n",
    "    plt.ylabel('Lift coefficient, $C_{l}$')\n",
    "    plt.grid()\n",
    "    plt.tight_layout() \n",
    "    plt.legend(['Experiment','Turbulent','Transition'])\n",
    "    \n",
    "\n",
    "    plt.subplot(1, 3, 2)\n",
    "    plt.plot(clcd['DU00W212']['cd'],clcd['DU00W212']['cl'],'ko')\n",
    "    plt.plot(cfd_turb['du00w212_F']['cd'],cfd_turb['du00w212_F']['cl'],'--')\n",
    "    plt.plot(cfd_trans['du00w212_F']['cd'],cfd_trans['du00w212_F']['cl'])\n",
    "    plt.xlabel('Drag coefficient, $C_{d}$')\n",
    "    plt.ylabel('Lift coefficient, $C_{l}$')\n",
    "    plt.xlim([0.0,0.03])\n",
    "    plt.ylim([-1, 2])\n",
    "    plt.grid()\n",
    "    plt.tight_layout() \n",
    "\n",
    "\n",
    "    plt.subplot(1, 3, 3)\n",
    "    plt.plot(clcd['DU00W212']['aoa'],clcd['DU00W212']['cm'],'ko')\n",
    "    plt.plot(cfd_turb['du00w212_F']['aoa'],np.array(cfd_turb['du00w212_F']['cm'])*-1,'--')\n",
    "    plt.plot(cfd_trans['du00w212_F']['aoa'],np.array(cfd_trans['du00w212_F']['cm'])*-1)\n",
    "    plt.xlabel('Angle of Attack [deg]')\n",
    "    plt.ylabel('Pitching moment coefficient, $C_{m}$')\n",
    "    plt.xlim([-10, 20])\n",
    "    plt.ylim([-0.12, -0.02])\n",
    "    plt.grid()\n",
    "    plt.tight_layout() \n",
    "\n",
    "    # plt.savefig(\"du_rey_%dM.png\"%re,dpi=300)\n",
    "\n",
    "plt.show()"
   ]
  }
 ],
 "metadata": {
  "language_info": {
   "name": "python"
  }
 },
 "nbformat": 4,
 "nbformat_minor": 2
}