{
 "cells": [
  {
   "cell_type": "markdown",
   "id": "2e0d0954",
   "metadata": {},
   "source": [
    "# Finite Wing with OOP (FiniteWing)\n",
    "\n",
    "This notebook recreates the finite wing workflow using the `FiniteWing` class from `src/aerodemo`."
   ]
  },
  {
   "cell_type": "markdown",
   "id": "cc7c501e",
   "metadata": {},
   "source": [
    "## Python project setup\n",
    "\n",
    "Configure Python paths so modules in `src/` are discoverable in a clean, explicit way."
   ]
  },
  {
   "cell_type": "code",
   "execution_count": 1,
   "id": "7a30c74c",
   "metadata": {},
   "outputs": [
    {
     "name": "stdout",
     "output_type": "stream",
     "text": [
      "Setting up environment...\n",
      "Notebook directory: F:\\agodemar\\AeroDemonstrator\\notebooks\\02_finite_wing\n",
      "Project root: F:\\agodemar\\AeroDemonstrator\n",
      "Using src path: F:\\agodemar\\AeroDemonstrator\\src\n",
      "Using aerodemo module path: F:\\agodemar\\AeroDemonstrator\\src\\aerodemo\n"
     ]
    }
   ],
   "source": [
    "import os\n",
    "import sys\n",
    "from pathlib import Path\n",
    "\n",
    "print(\"Setting up environment...\")\n",
    "this_notebook_dir = Path.cwd().resolve()\n",
    "project_root = (this_notebook_dir / \"..\" / \"..\").resolve()\n",
    "src_root = project_root / \"src\"\n",
    "aerodemo_root = src_root / \"aerodemo\"\n",
    "\n",
    "print(f\"Notebook directory: {this_notebook_dir}\")\n",
    "print(f\"Project root: {project_root}\")\n",
    "\n",
    "if not src_root.is_dir():\n",
    "    raise FileNotFoundError(f\"Could not find src directory at: {src_root}\")\n",
    "if not aerodemo_root.is_dir():\n",
    "    raise FileNotFoundError(f\"Could not find aerodemo directory at: {aerodemo_root}\")\n",
    "\n",
    "# Add both roots: src for package imports, src/aerodemo for module-style imports\n",
    "for p in (src_root, aerodemo_root):\n",
    "    p_str = str(p)\n",
    "    if p_str not in sys.path:\n",
    "        sys.path.insert(0, p_str)\n",
    "\n",
    "print(f\"Using src path: {src_root}\")\n",
    "print(f\"Using aerodemo module path: {aerodemo_root}\")"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": 2,
   "id": "75cff461",
   "metadata": {},
   "outputs": [
    {
     "name": "stdout",
     "output_type": "stream",
     "text": [
      "Successfully imported FiniteWing, WingSegment, and AirfoilSpec.\n"
     ]
    }
   ],
   "source": [
    "# Import OOP wing builder and related types\n",
    "import FiniteWing as finitewing_module\n",
    "from FiniteWing import FiniteWing\n",
    "from WingSegment import WingSegment\n",
    "from AirfoilSpec import AirfoilSpec\n",
    "\n",
    "# OpenVSP handle used by FiniteWing module\n",
    "vsp = finitewing_module.vsp\n",
    "\n",
    "print(\"Successfully imported FiniteWing, WingSegment, and AirfoilSpec.\")"
   ]
  },
  {
   "cell_type": "markdown",
   "id": "d7cfce77",
   "metadata": {},
   "source": [
    "## Build wing geometry with FiniteWing"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": 3,
   "id": "154a0d6c",
   "metadata": {},
   "outputs": [
    {
     "name": "stdout",
     "output_type": "stream",
     "text": [
      "FiniteWing:\n",
      "  name: FW_OOP_01\n",
      "  wing_id: None\n",
      "  mirrored: True\n",
      "  root_incidence_deg: 0.000 deg\n",
      "  rotate_airfoils_with_dihedral: True\n",
      "  root_cap_shape: Flat\n",
      "  tip_cap_shape: Round\n",
      "  root_cap_length: 0.000 m\n",
      "  tip_cap_length: 0.200 m\n",
      "  root_cap_strength: 1.000 (-)\n",
      "  tip_cap_strength: 1.000 (-)\n",
      "  location_xyz: (0.000, 0.000, 0.000) m\n",
      "  rotation_xyz: (0.000, 0.000, 0.000) deg\n",
      "  clear_model_first: True\n",
      "  num_segments: 2\n",
      "  segments:\n",
      "    WingSegment:\n",
      "      id: WS_INNER\n",
      "      span: 7.000 m\n",
      "      root_chord: 2.000 m\n",
      "      tip_chord: 2.000 m\n",
      "      sweep_deg: 0.000 deg\n",
      "      dihedral_deg: 0.000 deg\n",
      "      twist_deg: -2.000 deg\n",
      "      sweep_ref_loc: 0.250 (-)\n",
      "      twist_ref_loc: 0.250 (-)\n",
      "      num_U: 10 (-)\n",
      "      cluster_root: 1.000 (-)\n",
      "      cluster_tip: 1.000 (-)\n",
      "    WingSegment:\n",
      "      id: WS_OUTER\n",
      "      span: 7.000 m\n",
      "      root_chord: 2.000 m\n",
      "      tip_chord: 1.200 m\n",
      "      sweep_deg: 0.000 deg\n",
      "      dihedral_deg: 0.000 deg\n",
      "      twist_deg: -4.000 deg\n",
      "      sweep_ref_loc: 0.250 (-)\n",
      "      twist_ref_loc: 0.250 (-)\n",
      "      num_U: 16 (-)\n",
      "      cluster_root: 1.000 (-)\n",
      "      cluster_tip: 0.200 (-)\n",
      "  num_station_airfoils: 3\n",
      "  station_airfoils:\n",
      "    AirfoilSpec:\n",
      "      kind: naca4\n",
      "      thickness: 0.120 (-)\n",
      "      camber: 0.020 (-)\n",
      "      camber_loc: 0.400 x/c\n",
      "      sharp_te: True\n",
      "      file_path: None\n",
      "      xsec_type: None\n",
      "      extra_parms: {}\n",
      "    AirfoilSpec:\n",
      "      kind: naca4\n",
      "      thickness: 0.120 (-)\n",
      "      camber: 0.020 (-)\n",
      "      camber_loc: 0.400 x/c\n",
      "      sharp_te: True\n",
      "      file_path: None\n",
      "      xsec_type: None\n",
      "      extra_parms: {}\n",
      "    AirfoilSpec:\n",
      "      kind: naca4\n",
      "      thickness: 0.100 (-)\n",
      "      camber: 0.000 (-)\n",
      "      camber_loc: 0.400 x/c\n",
      "      sharp_te: True\n",
      "      file_path: None\n",
      "      xsec_type: None\n",
      "      extra_parms: {}\n"
     ]
    }
   ],
   "source": [
    "c_r  = 2.0  # m\n",
    "c_t  = 1.2  # m\n",
    "span = 14.0 # m\n",
    "dihedral_deg = 0.0 # deg\n",
    "\n",
    "# Define twist values relative to rigging angle, and compute absolute twist values\n",
    "rigging_deg = 0.0 # deg\n",
    "twist_rel_1_deg = -2.0 # deg\n",
    "twist_1_deg = rigging_deg + twist_rel_1_deg\n",
    "twist_rel_2_deg = -2.0 # deg\n",
    "twist_2_deg = rigging_deg + twist_rel_1_deg + twist_rel_2_deg\n",
    "\n",
    "segments = [\n",
    "    WingSegment(\n",
    "        id=\"WS_INNER\",\n",
    "        span=span/2,\n",
    "        root_chord=c_r,\n",
    "        tip_chord=c_r,\n",
    "        sweep_deg=0.0,\n",
    "        dihedral_deg=dihedral_deg,\n",
    "        twist_deg=twist_1_deg,\n",
    "        num_U=10, # Optional: set number of chordwise points for this segment\n",
    "        cluster_root=1.0, # Optional: cluster points towards root (0.0 to 1.0)\n",
    "        cluster_tip=1.0, # Optional: cluster points towards tip (0.0 to 1.0)\n",
    "    ),\n",
    "    WingSegment(\n",
    "        id=\"WS_OUTER\",\n",
    "        span=span/2,\n",
    "        root_chord=c_r,\n",
    "        tip_chord=c_t,\n",
    "        sweep_deg=0.0,\n",
    "        dihedral_deg=dihedral_deg,\n",
    "        twist_deg=twist_2_deg,\n",
    "        num_U=16, # Optional: set number of chordwise points for this segment\n",
    "        cluster_root=1.0, # Optional: cluster points towards root (0.0 to 1.0)\n",
    "        cluster_tip=0.2, # Optional: cluster points towards tip (0.0 to 1.0)\n",
    "    )\n",
    "]\n",
    "\n",
    "station_airfoils = [\n",
    "    AirfoilSpec(kind=\"naca4\", camber=0.02, camber_loc=0.4, thickness=0.12),\n",
    "    AirfoilSpec(kind=\"naca4\", camber=0.02, camber_loc=0.4, thickness=0.12),\n",
    "    AirfoilSpec(kind=\"naca4\", camber=0.00, camber_loc=0.4, thickness=0.10),\n",
    "]\n",
    "\n",
    "wing = FiniteWing(\n",
    "    name=\"FW_OOP_01\",\n",
    "    mirrored=True,\n",
    "    segments=segments,\n",
    "    station_airfoils=station_airfoils,\n",
    "    root_incidence_deg=rigging_deg,\n",
    "    tip_cap_shape=\"Round\",\n",
    "    tip_cap_length=0.20,\n",
    ")\n",
    "\n",
    "print(wing)"
   ]
  },
  {
   "cell_type": "markdown",
   "id": "044042f7",
   "metadata": {},
   "source": [
    "## Build and save outputs"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": 4,
   "id": "e2a5123d",
   "metadata": {},
   "outputs": [
    {
     "name": "stdout",
     "output_type": "stream",
     "text": [
      "Built wing geometry ID: KWJRABRPTV\n",
      "Saved model to: F:\\agodemar\\AeroDemonstrator\\notebooks\\02_finite_wing\\01_finite_wing_vsp_oop\\01_finite_wing_oop.vsp3\n"
     ]
    }
   ],
   "source": [
    "# Store all notebook outputs in a dedicated local folder\n",
    "output_dir = this_notebook_dir / \"01_finite_wing_vsp_oop\"\n",
    "output_dir.mkdir(parents=True, exist_ok=True)\n",
    "\n",
    "wing_id = wing.build()\n",
    "print(f\"Built wing geometry ID: {wing_id}\")\n",
    "\n",
    "vsp3_path = output_dir / \"01_finite_wing_oop.vsp3\"\n",
    "wing.save(str(vsp3_path))\n",
    "print(f\"Saved model to: {vsp3_path}\")"
   ]
  },
  {
   "cell_type": "markdown",
   "id": "a8b2cf5d",
   "metadata": {},
   "source": [
    "## Run VSPAero and save analysis files"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": 5,
   "id": "2356ede8",
   "metadata": {},
   "outputs": [
    {
     "name": "stdout",
     "output_type": "stream",
     "text": [
      "================= Results:\n",
      "\tExecuting compute geometry...\n",
      "\tCOMPLETE\n",
      "\tExecuting aero-sweep-analysis...\n",
      "\tCOMPLETE\n",
      "\n",
      "Saved CSV to: F:\\agodemar\\AeroDemonstrator\\notebooks\\02_finite_wing\\01_finite_wing_vsp_oop\\01_finite_wing_oop_analysis_results.csv\n",
      "Files in output directory:\n",
      "  - 01_finite_wing_oop.adb\n",
      "  - 01_finite_wing_oop.adb.cases\n",
      "  - 01_finite_wing_oop.case.1.quad.1.dat\n",
      "  - 01_finite_wing_oop.csf\n",
      "  - 01_finite_wing_oop.cuts\n",
      "  - 01_finite_wing_oop.group.0\n",
      "  - 01_finite_wing_oop.group.1\n",
      "  - 01_finite_wing_oop.history\n",
      "  - 01_finite_wing_oop.lod\n",
      "  - 01_finite_wing_oop.polar\n",
      "  - 01_finite_wing_oop.quad.cases\n",
      "  - 01_finite_wing_oop.slc\n",
      "  - 01_finite_wing_oop.vkey\n",
      "  - 01_finite_wing_oop.vsp3\n",
      "  - 01_finite_wing_oop.vspaero\n",
      "  - 01_finite_wing_oop.vspgeom\n",
      "  - 01_finite_wing_oop_analysis_results.csv\n"
     ]
    }
   ],
   "source": [
    "import io\n",
    "from contextlib import redirect_stdout\n",
    "\n",
    "previous_cwd = Path.cwd()\n",
    "os.chdir(output_dir)\n",
    "try:\n",
    "    # Compute geometry\n",
    "    vsp.SetAnalysisInputDefaults(\"VSPAEROComputeGeometry\")\n",
    "    vsp.SetIntAnalysisInput(\"VSPAEROComputeGeometry\", \"GeomSet\", [vsp.SET_NONE], 0)\n",
    "    vsp.SetIntAnalysisInput(\"VSPAEROComputeGeometry\", \"ThinGeomSet\", [vsp.SET_ALL], 0)\n",
    "\n",
    "    buf = io.StringIO()\n",
    "    with redirect_stdout(buf):\n",
    "        print(\"\\tExecuting compute geometry...\")\n",
    "        compgeom_resid = vsp.ExecAnalysis(\"VSPAEROComputeGeometry\")\n",
    "        print(\"\\tCOMPLETE\")\n",
    "        vsp.PrintResults(compgeom_resid)\n",
    "\n",
    "        # Sweep setup\n",
    "        vsp.SetAnalysisInputDefaults(\"VSPAEROSweep\")\n",
    "        vsp.SetIntAnalysisInput(\"VSPAEROSweep\", \"GeomSet\", [vsp.SET_NONE], 0)\n",
    "        vsp.SetIntAnalysisInput(\"VSPAEROSweep\", \"ThinGeomSet\", [vsp.SET_ALL], 0)\n",
    "        vsp.SetIntAnalysisInput(\"VSPAEROSweep\", \"RefFlag\", [1], 0)\n",
    "        vsp.SetIntAnalysisInput(\"VSPAEROSweep\", \"Symmetry\", [1], 0)\n",
    "\n",
    "        wid = vsp.FindGeomsWithName(\"FW_OOP_01\")\n",
    "        if not wid:\n",
    "            wid = vsp.FindGeomsWithName(\"WingGeom\")\n",
    "        vsp.SetStringAnalysisInput(\"VSPAEROSweep\", \"WingID\", wid, 0)\n",
    "\n",
    "        vsp.SetDoubleAnalysisInput(\"VSPAEROSweep\", \"AlphaStart\", [1.0], 0)\n",
    "        vsp.SetIntAnalysisInput(\"VSPAEROSweep\", \"AlphaNpts\", [1], 0)\n",
    "        vsp.SetDoubleAnalysisInput(\"VSPAEROSweep\", \"MachStart\", [0.1], 0)\n",
    "        vsp.SetIntAnalysisInput(\"VSPAEROSweep\", \"MachNpts\", [1], 0)\n",
    "        vsp.SetIntAnalysisInput(\"VSPAEROSweep\", \"WakeNumIter\", [8], 0)\n",
    "\n",
    "        vsp.Update()\n",
    "        print(\"\\tExecuting aero-sweep-analysis...\")\n",
    "        rid = vsp.ExecAnalysis(\"VSPAEROSweep\")\n",
    "        print(\"\\tCOMPLETE\")\n",
    "        vsp.PrintResults(rid)\n",
    "\n",
    "        csv_file_path = output_dir / \"01_finite_wing_oop_analysis_results.csv\"\n",
    "        vsp.WriteResultsCSVFile(rid, str(csv_file_path))\n",
    "\n",
    "    captured_logs = buf.getvalue()\n",
    "    print(\"================= Results:\")\n",
    "    print(captured_logs)\n",
    "    print(f\"Saved CSV to: {csv_file_path}\")\n",
    "\n",
    "    generated = sorted([p.name for p in output_dir.iterdir() if p.is_file()])\n",
    "    print(\"Files in output directory:\")\n",
    "    for name in generated:\n",
    "        print(f\"  - {name}\")\n",
    "finally:\n",
    "    os.chdir(previous_cwd)"
   ]
  }
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