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NASA SC(2)-1010 AIRFOIL

Symmetric · 10% thick · low-to-mid Re
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PROFILENASA SC(2)-1010 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness10.0% @ 33%c
max camber-4.5% @ 100%c
LE radius1.10%c
area upper / chord0.0280
area lower / chord-0.0388
area camber / chord-0.0054
TE thickness0.61%c
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Polars

Preliminary
NeuralFoil
0.08131-50.82663.3331.57211.672.31720ClAngle 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.

Geometry fit: RMS error 0.01378% of chord; maximum error 0.04951%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
143.6
Angle at maximum lift / drag (°)
6
Minimum Cd
0.007421
Maximum Cl
2.131
Angle at maximum Cl (°)
13
Cd at zero lift
—
Cm at zero angle
-0.1573
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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