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NACA M7 AIRFOIL

Cambered · 6% thick · low-to-mid Re
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PROFILENACA M7 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness6.2% @ 39%c
max camber5.0% @ 30%c
LE radius0.42%c
area upper / chord0.0485
area lower / chord0.0042
area camber / chord0.0264
TE thickness0.47%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.5431-50.082533.3330.708111.671.33420ClAngle 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 0.05789% of chord; maximum error 0.2861%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
123.4
Angle at maximum lift / drag (°)
6
Minimum Cd
0.006716
Maximum Cl
1.177
Angle at maximum Cl (°)
18
Cd at zero lift
0.02266
Cm at zero angle
-0.004114
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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