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NACA 5-DIGITSELIG-DATABASESYMMETRIC

NACA 63012A AIRFOIL

Symmetric · 12% thick · low-to-mid Re
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PROFILENACA 63012A AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness12.0% @ 35%c
max camber0.0% @ 0%c
LE radius1.58%c
area upper / chord0.0395
area lower / chord-0.0395
area camber / chord0.0000
TE thickness0.05%c
DOWNLOAD COORDINATES

Polars

Preliminary
Combined estimate
-0.8025-50.088543.3330.979511.671.87120ClAngle 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 0.0196% of chord; maximum error 0.1065%.

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
119.3
Angle at maximum lift / drag (°)
11
Minimum Cd
0.00704
Maximum Cl
1.648
Angle at maximum Cl (°)
17
Cd at zero lift
0.00704
Cm at zero angle
-1.144e-17
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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