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CAMBEREDNACA OTHERSELIG-DATABASE

NACA 1-H-15 AIRFOIL

Cambered · 15% thick · low-to-mid Re
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PROFILENACA 1-H-15 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness14.7% @ 40%c
max camber5.5% @ 40%c
LE radius2.39%c
area upper / chord0.0790
area lower / chord-0.0169
area camber / chord0.0311
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
Combined estimate
-0.37-50.25823.3330.886311.671.51520ClAngle 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 0.08592% of chord; maximum error 0.3068%.

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
85.08
Angle at maximum lift / drag (°)
4
Minimum Cd
0.007398
Maximum Cl
1.357
Angle at maximum Cl (°)
10
Cd at zero lift
0.00761
Cm at zero angle
-0.0586
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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