Airfoils.Pro
database / NACA 5-digit / NACA 63-412 AIRFOIL
CAMBEREDNACA 5-DIGITSELIG-DATABASE

NACA 63-412 AIRFOIL

Cambered · 12% thick · low-to-mid Re
Compare↓ Download
PROFILENACA 63-412 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness12.0% @ 35%c
max camber2.2% @ 50%c
LE radius1.58%c
area upper / chord0.0537
area lower / chord-0.0217
area camber / chord0.0160
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.4019-50.1683.3330.73811.671.30820ClAngle of attack (°)
Why this curve

This is a NeuralFoil prediction from the stored profile coordinates and the selected flow condition, with AeroSandbox compressibility corrections. It is not a completed OpenFOAM calculation.

Prediction error has not been calibrated for this condition. No accuracy interval is claimed.

The compressibility correction is a low-fidelity estimate, not a resolved shock or compressible CFD solution.

Geometry fit: RMS error 0.02459% of chord; maximum error 0.1173%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
138.7
Angle at maximum lift / drag (°)
5
Minimum Cd
0.006267
Maximum Cl
1.165
Angle at maximum Cl (°)
7
Cd at zero lift
0.006268
Cm at zero angle
-0.09113
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…