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NACA M19 AIRFOIL

Cambered · 6% thick · low-to-mid Re
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PROFILENACA M19 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness6.2% @ 30%c
max camber6.0% @ 30%c
LE radius0.42%c
area upper / chord0.0554
area lower / chord0.0115
area camber / chord0.0334
TE thickness0.38%c
DOWNLOAD COORDINATES

Polars

Preliminary
Combined estimate
-0.309-50.3763.3331.06111.671.74620ClAngle 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 0.05937% of chord; maximum error 0.3205%.

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
156.9
Angle at maximum lift / drag (°)
8
Minimum Cd
0.006276
Maximum Cl
1.575
Angle at maximum Cl (°)
10
Cd at zero lift
0.009186
Cm at zero angle
-0.05337
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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