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NASA SC(2)-0403 AIRFOIL

Symmetric · 3% thick · low-to-mid Re
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PROFILENASA SC(2)-0403 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness3.0% @ 36%c
max camber0.4% @ 82%c
LE radius0.10%c
area upper / chord0.0113
area lower / chord-0.0090
area camber / chord0.0012
TE thickness0.24%c
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Polars

Preliminary
NeuralFoil
-0.6079-50.022893.3330.653711.671.28520ClAngle 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 0.00498% of chord; maximum error 0.03406%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
92.92
Angle at maximum lift / drag (°)
4
Minimum Cd
0.00553
Maximum Cl
1.127
Angle at maximum Cl (°)
18
Cd at zero lift
0.005557
Cm at zero angle
-0.04683
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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