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CAMBEREDNACA OTHERSELIG-DATABASE

NACA 5-H-10 AIRFOIL

Cambered · 10% thick · low-to-mid Re
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PROFILENACA 5-H-10 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness9.9% @ 40%c
max camber2.2% @ 39%c
LE radius1.08%c
area upper / chord0.0441
area lower / chord-0.0219
area camber / chord0.0111
TE thickness0.00%c
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Polars

Preliminary
NeuralFoil
-0.6987-5-0.082813.3330.533111.671.14920ClAngle 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 0.05436% of chord; maximum error 0.2332%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
119.9
Angle at maximum lift / drag (°)
6
Minimum Cd
0.006083
Maximum Cl
0.995
Angle at maximum Cl (°)
8
Cd at zero lift
0.006091
Cm at zero angle
0.005087
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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