{
  "parameters": {
    "speed_m_s": 44.704,
    "speed_mph": 100,
    "angle_of_attack_deg": 0,
    "rho_kg_m3": 1.225,
    "nu_m2_s": 1.46e-05,
    "turbulence_intensity": 0.01,
    "turbulence_length_m": 0.1,
    "inlet_k_m2_s2": 0.2997671424,
    "inlet_omega_s_inv": 9.99611828661506,
    "wing_reference_area_full_m2": 22.815892,
    "wing_reference_area_half_m2": 11.407946,
    "reference_chord_m": 1.5594851815398076,
    "moment_reference_m": [
      -1.5,
      0,
      2.3
    ],
    "moment_reference_is_CG": false,
    "solver": "OpenFOAM v2512 simpleFoam bounded steady SST RANS; optional short pimpleFoam SST URANS check",
    "symmetry": "Y=0 half aircraft; integrals doubled for full-airframe dimensional forces; Aref half for force coefficients",
    "propellers": "Blades omitted; stationary cruise-oriented nacelles/booms/hubs retained. No propulsion model.",
    "geometry_sha256": "7268f5d8e9ba890d85becf4764d381de9b5905fe7f8956987561a444face1963",
    "geometry_cleaning": "25 mm voxel union with two smoothing passes; thin trailing edges rounded",
    "purpose": "Initial airframe pressure/drag and separated-flow screening, not OEM performance, stall or certification",
    "cpu_cap": 44,
    "near_wall_strategy": "Wall-function RANS on surface-refined snapped cells. No prism layers; boundary-layer profiles and skin-friction accuracy unresolved. Actual yPlus audited.",
    "domain_m": {
      "min": [
        -35,
        0,
        -30
      ],
      "max": [
        75,
        35,
        35
      ]
    },
    "expected_outputs": [
      "native Intel case fields and logs",
      "force and coefficient histories",
      "mesh and numerical audits",
      "fixed-aircraft lift/drag videos through 20 degrees",
      "editable Blender field visualization"
    ],
    "angles_deg": [
      0,
      2,
      4,
      6,
      8,
      10,
      12,
      14,
      16,
      18,
      20
    ],
    "mesh_improvements": "Refined near field and high-angle wake; wing/tail/nacelle level 7 surfaces; no prism layers; 15 tiny fluid cells closed. Configured checks pass; expanded concave-cell diagnostic remains.",
    "aggregate_cpu_cap": 44,
    "meshing_ranks": 16,
    "geometry_scope": "Same public-source approximation, half-domain Y symmetry. No propulsion. No grid independence or OEM stall/flight-limit validation.",
    "cores_per_case": 4,
    "mesh_attempt": "Finer wing/tail/nacelle surface cells, no prism-layer extrusion; rejected layered and cell-splitting attempts retained",
    "spatial_convection": "bounded Gauss limitedLinearV 1 after 200 upwind conditioning steps",
    "maximum_steady_iterations": 1000,
    "mean_window_iterations": 200,
    "unsteady_mean_start_s": 0.03,
    "unsteady_max_time_s": 0.4,
    "unsteady_wall_budget_s": 1800
  },
  "cases": [
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      "mean_window": 200,
      "Cd_mean": 0.045545020333969566,
      "Cl_mean": -0.04828955466684957,
      "Cd_relative_range": 0.008469840208045015,
      "Cl_absolute_range": 0.0049750426,
      "residuals_last": {
        "Ux": 5.379897e-05,
        "Uy": 0.00015146402,
        "Uz": 0.00042128318,
        "p": 0.00026631389,
        "omega": 9.1401875e-07,
        "k": 1.2496488e-05
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      "residuals_pass": false,
      "force_history_pass": false,
      "relative_net_boundary_flux": 3.0388901795150182e-09,
      "mass_pass": true,
      "numerical_targets_met": false,
      "grid_independent": false,
      "needs_unsteady": true,
      "stop_requested": true,
      "qualification": "Steady criteria not met; a physical-time URANS check is required",
      "native_field_time": 1000,
      "surface_field_basis": "final p, U, wallShearStress iterate",
      "statistics_basis": "last 200 second-order solver iterations",
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          "drag_min_window_N": 1266.805754,
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          "lift_min_window_N": -1403.134458,
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        "fuselage": {
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          "viscous_drag_N": 64.52134114300003,
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          "drag_min_window_N": 371.03054,
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          "lift_min_window_N": -972.613274,
          "lift_max_window_N": -926.319506
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        "wing": {
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          "drag_min_window_N": 41.9000744,
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          "lift_min_window_N": -427.879914,
          "lift_max_window_N": -330.516326
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        "tail": {
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        "booms": {
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        "nacelles": {
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      "native_field_time": 1000,
      "surface_field_basis": "final p, U, wallShearStress iterate",
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      "native_field_time": 1000,
      "surface_field_basis": "final p, U, wallShearStress iterate",
      "statistics_basis": "last 200 second-order solver iterations",
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      "native_field_time": 1000,
      "surface_field_basis": "final p, U, wallShearStress iterate",
      "statistics_basis": "last 200 second-order solver iterations",
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        "nacelles": {
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        "gear": {
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      },
      "lift_N": 25632.25086809485,
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      "Cl_force_crosscheck_relative": 4.121704396429221e-06,
      "Cd_force_crosscheck_relative": 3.252085899725287e-06
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  ],
  "qualification": "Independent public-reference geometry, generic airfoils, unpowered half-domain with enforced symmetry. No OEM validation or grid/timestep independence. Mesh audit and case numerical criteria are disclosed separately. These results cannot establish the real aircraft stall angle or safe operating limits.",
  "statistics": "Steady cases: last 200 solver-iteration means/ranges. URANS cases: physical-time-weighted means/ranges beginning at 0.03 s. Surface fields follow the documented basis per case.",
  "force_arrows": "Integrated wind-axis forces, illustrative common anchor, not CG or center of pressure.",
  "maximum_sampled_lift": {
    "alpha_deg": 20,
    "lift_N": 25632.25086809485,
    "interpretation": "Maximum among sampled reconstructed-model cases only; not a validated stall angle. Numerical and model limitations apply."
  }
}