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NACA M13 AIRFOIL

Cambered · 6% thick · low-to-mid Re
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PROFILENACA M13 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness6.2% @ 30%c
max camber3.9% @ 30%c
LE radius0.42%c
area upper / chord0.0460
area lower / chord0.0017
area camber / chord0.0238
TE thickness0.44%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.4354-50.18913.3330.813611.671.43820ClAngle 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 0.04721% of chord; maximum error 0.24%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
145.8
Angle at maximum lift / drag (°)
6
Minimum Cd
0.006084
Maximum Cl
1.282
Angle at maximum Cl (°)
8
Cd at zero lift
0.00618
Cm at zero angle
-0.05699
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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