Problem
HiLiftAeroML
Fluid Dynamics 3D
A high-lift aircraft external-aero problem on open HiLiftAeroML geometries: change angle of attack plus flap and slat settings, then predict drag, lift, and pitching moment plus surface pressure coefficient (Cp) and wall shear on the aircraft skin. Ground truth is upstream CFD, not a re-run here. Landing and takeoff aero. Miss separation or stall and the lift curve and field metrics show it.
- Industry
- Aerospace
- Domain
- Fluid dynamics 3D
- Task
- Cp, wall shear + forces
- Datasets
- 1
Scope and limits
Comparability
High-lift aircraft external aero, not comparable with road-car DrivAerML or 2D airfoil packs. Scores are fair within this cleaned ~8M CAD-skin mesh. Do not mix with native-boundary or decimated variants if those land later.
Open cases
This site hosts the geometry_super_scarce_train slice (40 cases), not the full 1800-case HiLiftAeroML corpus. Strong scores here do not automatically mean strong performance on larger geometry or AoA splits.
Ground truth
CFD surface data from HiLiftAeroML (CC-BY-4.0). Upstream simulations used OpenFOAM. We did not re-run solvers on this site. Please cite HiLiftAeroML when you use this data.
Datasets
Open pack is geometry_super_scarce_train: four LHC geometries (043 / 049 / 083 / 131) × AoA 4–22° (40 cases) on a cleaned ~8M-node CAD skin.
1 live · 1 total
| Dataset | What varies | Geometry | Mesh | Solver | Cases | Runs | Open |
|---|---|---|---|---|---|---|---|
Geometry Super-Scarce Open · Live | AoA + eight flap/slat knobs | 4 LHC geos × 10 AoA | ~8M CAD skin | OpenFOAM | 40cases | — | Open |