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NACA OTHERSELIG-DATABASESYMMETRIC

NACA 0010-35

Symmetric · 10% thick · low-to-mid Re
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PROFILENACA 0010-35
surfacecamber line
GEOMETRY · AREA METRICS
max thickness10.0% @ 50%c
max camber0.0% @ 0%c
LE radius1.10%c
area upper / chord0.0362
area lower / chord-0.0362
area camber / chord0.0000
TE thickness0.20%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.7391-50.043413.3330.825911.671.60820ClAngle 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 0.04156% of chord; maximum error 0.1758%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
97.6
Angle at maximum lift / drag (°)
9
Minimum Cd
0.007086
Maximum Cl
1.413
Angle at maximum Cl (°)
15
Cd at zero lift
0.007086
Cm at zero angle
9.151e-17
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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