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NASA RC(4)-10 AIRFOIL

Cambered · 10% thick · low-to-mid Re
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PROFILENASA RC(4)-10 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness10.0% @ 38%c
max camber2.1% @ 30%c
LE radius1.10%c
area upper / chord0.0471
area lower / chord-0.0226
area camber / chord0.0122
TE thickness0.16%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.7058-50.19333.3331.09211.671.99220ClAngle 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 0.02093% of chord; maximum error 0.1154%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
127.7
Angle at maximum lift / drag (°)
10
Minimum Cd
0.00668
Maximum Cl
1.767
Angle at maximum Cl (°)
16
Cd at zero lift
0.006681
Cm at zero angle
-0.002292
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…