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NACA M6 AIRFOIL

Cambered · 12% thick · low-to-mid Re
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PROFILENACA M6 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness12.0% @ 30%c
max camber2.2% @ 30%c
LE radius1.59%c
area upper / chord0.0531
area lower / chord-0.0314
area camber / chord0.0108
TE thickness0.52%c
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Polars

Preliminary
NeuralFoil
-0.735-50.15043.3331.03611.671.92120ClAngle 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.

Geometry fit: RMS error 0.05794% of chord; maximum error 0.2931%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
121.1
Angle at maximum lift / drag (°)
11
Minimum Cd
0.007306
Maximum Cl
1.7
Angle at maximum Cl (°)
16
Cd at zero lift
0.007322
Cm at zero angle
0.002601
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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