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NASA SC(2)-0402 AIRFOIL

Symmetric · 2% thick · low-to-mid Re
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PROFILENASA SC(2)-0402 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness2.0% @ 35%c
max camber-0.5% @ 100%c
LE radius0.04%c
area upper / chord0.0071
area lower / chord-0.0065
area camber / chord0.0003
TE thickness0.19%c
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Polars

Preliminary
NeuralFoil
-0.5981-50.031333.3330.660711.671.2920ClAngle 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 0.003835% of chord; maximum error 0.02406%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
55.87
Angle at maximum lift / drag (°)
2
Minimum Cd
0.005445
Maximum Cl
1.133
Angle at maximum Cl (°)
17
Cd at zero lift
0.005543
Cm at zero angle
-0.04123
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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