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NACA M14 AIRFOIL

Cambered · 8% thick · low-to-mid Re
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PROFILENACA M14 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness8.1% @ 31%c
max camber4.0% @ 30%c
LE radius0.72%c
area upper / chord0.0532
area lower / chord-0.0043
area camber / chord0.0245
TE thickness0.42%c
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Polars

Preliminary
Combined estimate
-0.4311-50.20973.3330.850411.671.49120ClAngle of attack (°)
Why this curve

This curve combines the stored NeuralFoil prediction with 0 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 0.05329% of chord; maximum error 0.2969%.

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

Curve summary

Combined estimate · Within -5° to 20°

Maximum lift / drag
146.2
Angle at maximum lift / drag (°)
7
Minimum Cd
0.006236
Maximum Cl
1.331
Angle at maximum Cl (°)
8
Cd at zero lift
0.0063
Cm at zero angle
-0.06172
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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