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CAMBEREDNACA OTHERSELIG-DATABASETHICK

NACA 6-H-20 AIRFOIL

Cambered · 20% thick · low-to-mid Re
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PROFILENACA 6-H-20 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness19.9% @ 40%c
max camber6.1% @ 39%c
LE radius4.38%c
area upper / chord0.0969
area lower / chord-0.0366
area camber / chord0.0302
TE thickness0.00%c
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Polars

Preliminary
NeuralFoil
-0.5014-50.20633.3330.914111.671.62220ClAngle of attack (°)
Why this curve

This is a NeuralFoil prediction from the stored profile coordinates and the selected flow condition, with AeroSandbox compressibility corrections. It is not a completed OpenFOAM calculation.

Prediction error has not been calibrated for this condition. No accuracy interval is claimed.

The compressibility correction is a low-fidelity estimate, not a resolved shock or compressible CFD solution.

Geometry fit: RMS error 0.09757% of chord; maximum error 0.283%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
59.94
Angle at maximum lift / drag (°)
3
Minimum Cd
0.00799
Maximum Cl
1.445
Angle at maximum Cl (°)
14
Cd at zero lift
0.008033
Cm at zero angle
-0.002085
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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