Airfoils.Pro
database / NACA 5-digit / NACA 64012
NACA 5-DIGITSELIG-DATABASESYMMETRIC

NACA 64012

Symmetric · 12% thick · low-to-mid Re
Compare↓ Download
PROFILENACA 64012
surfacecamber line
GEOMETRY · AREA METRICS
max thickness12.0% @ 39%c
max camber0.0% @ 0%c
LE radius1.58%c
area upper / chord0.0379
area lower / chord-0.0379
area camber / chord0.0000
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.8174-50.086033.3330.989511.671.89320ClAngle 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.

Geometry fit: RMS error 0.02419% of chord; maximum error 0.1054%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
120.7
Angle at maximum lift / drag (°)
11
Minimum Cd
0.006894
Maximum Cl
1.667
Angle at maximum Cl (°)
16
Cd at zero lift
0.006894
Cm at zero angle
2.86e-17
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…