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NACA M10 AIRFOIL

Cambered · 6% thick · low-to-mid Re
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PROFILENACA M10 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness6.2% @ 30%c
max camber1.9% @ 30%c
LE radius0.42%c
area upper / chord0.0332
area lower / chord-0.0109
area camber / chord0.0112
TE thickness0.39%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.6514-50.22853.3331.10811.671.98820ClAngle 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 0.04271% of chord; maximum error 0.2234%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
126.6
Angle at maximum lift / drag (°)
9
Minimum Cd
0.006416
Maximum Cl
1.768
Angle at maximum Cl (°)
16
Cd at zero lift
0.006426
Cm at zero angle
-0.02542
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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