Airfoils.Pro
database / NACA 6-series / NACA 66(1)-212
CAMBEREDNACA 6-SERIESSELIG-DATABASE

NACA 66(1)-212

Cambered · 12% thick · low-to-mid Re
Compare↓ Download
PROFILENACA 66(1)-212
surfacecamber line
GEOMETRY · AREA METRICS
max thickness12.0% @ 45%c
max camber1.1% @ 50%c
LE radius1.59%c
area upper / chord0.0488
area lower / chord-0.0328
area camber / chord0.0080
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.6079-50.2173.3331.04211.671.86720ClAngle 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 0.02678% of chord; maximum error 0.1104%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
124.4
Angle at maximum lift / drag (°)
10
Minimum Cd
0.007072
Maximum Cl
1.661
Angle at maximum Cl (°)
16
Cd at zero lift
0.007079
Cm at zero angle
-0.0415
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…