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NACA M9 AIRFOIL

Cambered · 10% thick · low-to-mid Re
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PROFILENACA M9 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness10.4% @ 15%c
max camber7.2% @ 30%c
LE radius1.19%c
area upper / chord0.0674
area lower / chord0.0151
area camber / chord0.0413
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
Combined estimate
-0.3087-50.37973.3331.06811.671.75720ClAngle of attack (°)
Why this curve

This curve combines the stored NeuralFoil prediction with 1 contributing CFD observations. History windows remain observations, not separate solver runs or automatically converged points.

Model uncertainty is conditional on the stated assumptions and has not been calibrated for this condition. It is not a validated accuracy guarantee.

Geometry fit: RMS error 0.1051% of chord; maximum error 0.2922%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10 · Polar model progressive-polar-gp-v2

  • · Provisional history

Curve summary

Combined estimate · Within -5° to 20°

Maximum lift / drag
57.32
Angle at maximum lift / drag (°)
6
Minimum Cd
0.01801
Maximum Cl
1.585
Angle at maximum Cl (°)
9
Cd at zero lift
0.01962
Cm at zero angle
-0.0515
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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