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NACA M16 AIRFOIL

Cambered · 6% thick · low-to-mid Re
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PROFILENACA M16 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness6.1% @ 31%c
max camber4.1% @ 30%c
LE radius0.42%c
area upper / chord0.0441
area lower / chord0.0001
area camber / chord0.0221
TE thickness0.56%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.4649-50.16553.3330.795911.671.42620ClAngle 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 0.05082% of chord; maximum error 0.2772%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
142.7
Angle at maximum lift / drag (°)
7
Minimum Cd
0.00628
Maximum Cl
1.269
Angle at maximum Cl (°)
8
Cd at zero lift
0.00631
Cm at zero angle
-0.02686
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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