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HAM-STD HS1-606 AIRFOIL

Cambered · 6% thick · low-to-mid Re
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PROFILEHAM-STD HS1-606 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness6.0% @ 18%c
max camber4.2% @ 44%c
LE radius0.40%c
area upper / chord0.0502
area lower / chord0.0056
area camber / chord0.0279
TE thickness0.47%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.1468-50.4053.3330.956911.671.50920ClAngle 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 0.009512% of chord; maximum error 0.02897%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
160.1
Angle at maximum lift / drag (°)
5
Minimum Cd
0.006193
Maximum Cl
1.371
Angle at maximum Cl (°)
6
Cd at zero lift
0.00644
Cm at zero angle
-0.1409
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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