Aerospace - External Aerodynamics

2D Cases

NACA-0012 Airfoil

  • Experimental data: publically available
  • Grids: publically available
  • Numerical results: publically available
  • Cases:
    • M = 0.15
    • Re = 6E6
    • AoA = -17.3deg. to +17.3deg.

NACA-4412 Airfoil

  • Objective: Trailing edge separation.
  • Experimental data: publically available
  • Grids: publically available
  • Numerical results: publically available
  • Case:
    • M = 0.09
    • Re = 1.52E6
    • AoA = 13.87 deg.

RAE-2822 Airfoil

  • Experimental data: publically available
  • Grids: publically available
  • Numerical results: publically available
  • Case:
    • M = 0.725
    • Re = 6.5E6
    • AoA = 2.92 deg.

NLR Airfoil with Flap

  • Experimental data: publically available
  • Grids: publically available
  • Numerical results: publically available
  • Cases:
    • M = 0.20
      • P = 14.7 Psia
    • T = 520 R
    • AoA = 10 deg.

Axisymmetric SWBLI near M=7

  • Experimental data: publically available
  • Grids: not available
  • Numerical results: publically available
  • Case:
    • M = 7.11
    • Re = 57060 per cm
    • AoA = 20 deg.

3D Cases

Onera M6 Wing

  • Experimental data: publically available
  • Grids: not available
  • Numerical results: publically available
  • Case:
    • M = 0.8395
    • Re = 11.72E6
    • AoA = 3.06 deg.
  • CFL3D site

ARA M100 Wing-Body

  • Experimental data: publically available
  • Grids: not available
  • Numerical results: publically available
  • Case:
    • M = 0.8027
    • Re = 13.1E6
    • AoA = 2.873 deg.

Delta Wing

  • Experimental data: publically available
  • Grids: not available
  • Numerical results: publically available
  • Case:
    • M = 0.3
    • Re = 0.5E6
    • AoA = 20.5 deg.

DPW Series

DPW-1

  • Experimental data: publically available
  • Grids: not available
  • Numerical results: publically available
  • Case:
    • M = 0.8395
    • Re = 11.72E6
    • AoA = 3.06 deg.

DPW-2

  • 2nd AIAA CFD Drag Prediction Workshop
  • Model: DLR-F6
  • Experimental data: publically available
  • Grids: publically available
  • Numerical results: publically available
  • Cases (required):
    • Single point grid convergence study for wb and wbpn
      • M = 0.75
      • Re = 3E6 (c=141.2 mm)
      • CL = .500 ± .001
      • “Fully turbulent” solution
    • Drag Polar for wb and wbpn
      • M = 0.75
      • Re = 3E6 (c=141.2 mm)
      • AoA (deg.) = -3°, -2°, -1.5°, -1°,0°, 1°, 1.5°
      • Boundary layer transition or “fully turbulent”
  • Cases (optional):
    • Comparison of “tripped” and “fully turbulent” solutions
      • M = 0.75
      • Re = 3E6 (c=141.2 mm)
      • CL = .500 ± .001
    • Drag rise for for wb and wbpn (very optional)
      • M = 0.50, 0.60, 0.70, 0.72, 0.74, 0.75, 0.76, 0.77
      • CL = 0.500 ± .001

DPW-3

  • 3rd AIAA CFD Drag Prediction Workshop
  • Model: DLR-F6
  • Experimental data: publically available
  • Grids: publically available
  • Numerical results: publically available
  • Cases
    • DLR-F6 wb with and without FX2B fairing
      • For all cases
        • Re = 5E6 (cref = 141.2 mm)
        • T = 580R (322.22 K)
      • DLR-F6 wb with FX2B fairing and without fairing
        • Grid convergence study
          • M = 0.75
          • CL = 0.500 ±0.001
        • Drag polar (medium grid)
          • M = 0.75
          • AoA = -3, -2, -1, -0.5, 0, 0.5, 1, 1.5 deg.
    • Wing alone comparison: DPW-W1 (baseline) vs. DPW-W2 (simple optimization)
      • Re = 5E6 (cref = 197.556 mm)
      • T = 580R (322.22 K)
      • M = 0.76
      • Grid convergence
        • AoA = 0.5 deg.
      • Drag polar (medium grid)
        • AoA = -1, 0, 0.5, 1, 1.5, 2, 2.5, 3 deg.

DPW-4

  • 4th AIAA CFD Drag Prediction Workshop
  • Model: NASA Common Research Model (CRM)
  • Experimental data: publically available
  • Grids: publically available
  • Numerical results: publically available
  • Cases:
    • Grid convergence and downwash studies:
      • M=0.85
      • Re = 5E6 (cref = 275.80 in)
      • T = 100F
      • Grid convergence study
        • CL=0.500 ±0.001
      • Downwash study
        • Drag Polars for AoA = 0.0, 1.0, 1.5, 2.0, 2.5, 3.0, 4.0 deg.
        • Trimmed drag polar (cg at reference center) derived from polars at iH = -2, 0, +2 deg.
        • Delta drag polar of tail off vs. tail on (i.e. wb vs. wbh trimmed)
    • Mach sweep study (optional):
      • Re = 5E6 (cref = 275.80 in)
      • T = 100F
      • Drag Polars at M = 0.70, 0.75, 0.80, 0.83, 0.85, 0.86, 0.87
      • Drag rise curves at CL = 0.400, 0.450, 0.500 (±0.001 or extracted from polars)
    • Reynolds number study (optional):
      • Compare Re = 5E6 results with Re = 20E6 results (cref = 275.80 in)
      • M = 0.85
      • CL = 0.500 ±0.001
      • T = -250F (for Re = 20E6)

DPW-5

  • 5th AIAA CFD Drag Prediction Workshop
  • Model: NASA Common Research Model (CRM)
  • Experimental data: publically available
  • Grids: publically available
  • Numerical results: publically available
  • Cases:
    • Wing-body grid convergence study:
      • M = 0.85
      • CL = 0.500 ±0.001
      • Re = 5E6 (cref = 275.80 in)
      • T = 100F
      • Provided grid series (required)
      • Participant developed grids (optional)
    • Wing-body buffet study:
      • M = 0.85
      • Drag polar for AoA = 2.50, 2.75, 3.00, 3.25, 3.50, 3.75, 4.00 deg.
      • Re = 5E6 (cref = 275.80 in)
      • T = 100F

DPW-6

  • 6th AIAA CFD Drag Prediction Workshop
  • Model: NASA Common Research Model (CRM)
  • Experimental data: publically available
  • Grids: publically available
  • Numerical results: publically available
  • Cases:
    • M = 0.85
    • Re = 5E6
    • CL = 0.5 ±0.001

DPW-7

  • 7th AIAA CFD Drag Prediction Workshop
  • Model: NASA Common Research Model (CRM)
  • Experimental data: publically available
  • Grids: publically available
  • Numerical results: publically available
  • Cases:
    • Required
      • Case 1: Grid Convergence Study
      • Case 2: Alpha Sweeps at Constant Re
      • Case 3: Re Sweep at Constant CL
    • Optional
      • Case 4: Solution-Adapted Grid
      • Case 5: Beyond RANS: URANS, DDES, WMLES, Lattice-Boltzmann, etc.
      • Case 6: Coupled Aero-Structural Simulation

HLPW Series

HLPW-1

  • 1st AIAA CFD High Lift Prediction Workshop
  • Model: NASA Trap Wing
  • Experimental data: publically available
  • Grids: publically available
  • Numerical results: publically available
  • Cases

HLPW-2

  • 2nd AIAA CFD High Lift Prediction Workshop
  • Model: DLR F-11
  • Experimental data: publically available
  • Grids: publically available
  • Numerical results: publically available
  • Cases

HLPW-3

  • 3rd AIAA CFD High Lift Prediction Workshop
  • Model: JAXA JSM
  • Experimental data: publically available
  • Grids: publically available
  • Numerical results: publically available
  • Cases

HLPW-4

  • 4th AIAA CFD High Lift Prediction Workshop
  • Model: NASA CRM-HL
  • Experimental data: publically available
  • Grids: publically available
  • Numerical results: publically available
  • Cases

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