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NACA M25 AIRFOIL

Cambered · 6% thick · low-to-mid Re
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PROFILENACA M25 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness6.3% @ 30%c
max camber8.2% @ 30%c
LE radius0.43%c
area upper / chord0.0666
area lower / chord0.0218
area camber / chord0.0442
TE thickness0.45%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.2893-50.48273.3331.25511.672.02720ClAngle 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 0.07328% of chord; maximum error 0.3416%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
154.6
Angle at maximum lift / drag (°)
9
Minimum Cd
0.006868
Maximum Cl
1.834
Angle at maximum Cl (°)
11
Cd at zero lift
0.01909
Cm at zero angle
-0.04809
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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