Airfoils.Pro
database / NACA 6-series / NACA 66(4)-221
CAMBEREDNACA 6-SERIESSELIG-DATABASETHICK

NACA 66(4)-221

Cambered · 21% thick · low-to-mid Re
Compare↓ Download
PROFILENACA 66(4)-221
surfacecamber line
GEOMETRY · AREA METRICS
max thickness21.0% @ 45%c
max camber1.1% @ 50%c
LE radius4.86%c
area upper / chord0.0784
area lower / chord-0.0621
area camber / chord0.0082
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.5471-50.024963.3330.59711.671.16920ClAngle 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 0.04014% of chord; maximum error 0.1222%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
79.04
Angle at maximum lift / drag (°)
7
Minimum Cd
0.008045
Maximum Cl
1.026
Angle at maximum Cl (°)
9
Cd at zero lift
0.008054
Cm at zero angle
-0.03753
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…