Airfoils.Pro
database / NACA 6-series / NACA 65(1)-412
CAMBEREDNACA 6-SERIESSELIG-DATABASE

NACA 65(1)-412

Cambered · 12% thick · low-to-mid Re
Compare↓ Download
PROFILENACA 65(1)-412
surfacecamber line
GEOMETRY · AREA METRICS
max thickness12.0% @ 40%c
max camber2.2% @ 50%c
LE radius1.58%c
area upper / chord0.0549
area lower / chord-0.0228
area camber / chord0.0160
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.3943-50.16953.3330.733311.671.29720ClAngle 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 0.02943% of chord; maximum error 0.1095%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
137.8
Angle at maximum lift / drag (°)
5
Minimum Cd
0.006283
Maximum Cl
1.156
Angle at maximum Cl (°)
6
Cd at zero lift
0.006286
Cm at zero angle
-0.09432
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…