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NACA M24 AIRFOIL

Cambered · 12% thick · low-to-mid Re
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PROFILENACA M24 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness11.9% @ 31%c
max camber6.3% @ 30%c
LE radius1.57%c
area upper / chord0.0748
area lower / chord-0.0090
area camber / chord0.0329
TE thickness0.47%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.3715-50.37633.3331.12411.671.87220ClAngle 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 0.07244% of chord; maximum error 0.3412%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
134.9
Angle at maximum lift / drag (°)
8
Minimum Cd
0.006947
Maximum Cl
1.685
Angle at maximum Cl (°)
12
Cd at zero lift
0.008569
Cm at zero angle
-0.01611
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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