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CAMBEREDNACA OTHERSELIG-DATABASETHICK

NACA 6-H-15 AIRFOIL

Cambered · 16% thick · low-to-mid Re
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PROFILENACA 6-H-15 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness15.6% @ 40%c
max camber4.5% @ 39%c
LE radius2.67%c
area upper / chord0.0729
area lower / chord-0.0281
area camber / chord0.0224
TE thickness0.00%c
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Polars

Preliminary
Combined estimate
-0.6178-50.079523.3330.776911.671.47420ClAngle 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 0.07091% of chord; maximum error 0.296%.

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
116.5
Angle at maximum lift / drag (°)
8
Minimum Cd
0.007
Maximum Cl
1.3
Angle at maximum Cl (°)
10
Cd at zero lift
0.007008
Cm at zero angle
0.01043
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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