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NASA/LANGLEY RC-10(N)1 AIRFOIL

Cambered · 10% thick · low-to-mid Re
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PROFILENASA/LANGLEY RC-10(N)1 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness10.0% @ 37%c
max camber1.5% @ 26%c
LE radius1.10%c
area upper / chord0.0410
area lower / chord-0.0249
area camber / chord0.0081
TE thickness0.16%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.7422-5-0.12873.3330.484811.671.09820ClAngle 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 0.01753% of chord; maximum error 0.1088%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
116.4
Angle at maximum lift / drag (°)
6
Minimum Cd
0.006073
Maximum Cl
0.945
Angle at maximum Cl (°)
17
Cd at zero lift
0.006103
Cm at zero angle
0.007816
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…