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NACA M11 AIRFOIL

Cambered · 8% thick · low-to-mid Re
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PROFILENACA M11 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness8.1% @ 30%c
max camber1.9% @ 30%c
LE radius0.73%c
area upper / chord0.0392
area lower / chord-0.0178
area camber / chord0.0107
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.6637-50.19213.3331.04811.671.90420ClAngle 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 0.04994% of chord; maximum error 0.2733%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
123.6
Angle at maximum lift / drag (°)
10
Minimum Cd
0.006516
Maximum Cl
1.69
Angle at maximum Cl (°)
16
Cd at zero lift
0.006517
Cm at zero angle
-0.0119
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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