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NACA M22 AIRFOIL

Cambered · 6% thick · low-to-mid Re
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PROFILENACA M22 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness6.2% @ 31%c
max camber6.3% @ 30%c
LE radius0.43%c
area upper / chord0.0552
area lower / chord0.0104
area camber / chord0.0328
TE thickness0.53%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.3571-50.33873.3331.03411.671.7320ClAngle 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 0.06382% of chord; maximum error 0.3136%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
150.8
Angle at maximum lift / drag (°)
8
Minimum Cd
0.00653
Maximum Cl
1.556
Angle at maximum Cl (°)
10
Cd at zero lift
0.008568
Cm at zero angle
-0.01854
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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