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NACA M18 AIRFOIL

Cambered · 12% thick · low-to-mid Re
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PROFILENACA M18 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness12.0% @ 30%c
max camber4.2% @ 30%c
LE radius1.59%c
area upper / chord0.0651
area lower / chord-0.0190
area camber / chord0.0230
TE thickness0.44%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.5008-50.18163.3330.86411.671.54620ClAngle 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 0.06288% of chord; maximum error 0.3276%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
135.3
Angle at maximum lift / drag (°)
8
Minimum Cd
0.006702
Maximum Cl
1.376
Angle at maximum Cl (°)
10
Cd at zero lift
0.006704
Cm at zero angle
-0.02457
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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