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NASA SC(2)-0010 AIRFOIL

Symmetric · 10% thick · low-to-mid Re
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PROFILENASA SC(2)-0010 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness10.0% @ 37%c
max camber0.0% @ 0%c
LE radius1.10%c
area upper / chord0.0355
area lower / chord-0.0355
area camber / chord0.0000
TE thickness0.50%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.8323-50.10243.3331.03711.671.97220ClAngle 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 0.01155% of chord; maximum error 0.04352%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
125.3
Angle at maximum lift / drag (°)
11
Minimum Cd
0.006894
Maximum Cl
1.738
Angle at maximum Cl (°)
17
Cd at zero lift
0.006894
Cm at zero angle
-1.773e-16
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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