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HAM-STD HS1-620 AIRFOIL

Cambered · 20% thick · low-to-mid Re
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PROFILEHAM-STD HS1-620 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness20.0% @ 35%c
max camber4.1% @ 44%c
LE radius4.41%c
area upper / chord0.1052
area lower / chord-0.0476
area camber / chord0.0288
TE thickness2.70%c
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Polars

Preliminary
NeuralFoil
-0.156-50.50733.3331.17111.671.83420ClAngle 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 0.01397% of chord; maximum error 0.03675%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
116.9
Angle at maximum lift / drag (°)
6
Minimum Cd
0.008836
Maximum Cl
1.668
Angle at maximum Cl (°)
10
Cd at zero lift
—
Cm at zero angle
-0.1482
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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