Airfoils.Pro
database / NACA 5-digit / NACA 66-021 AIRFOIL
NACA 5-DIGITSELIG-DATABASESYMMETRICTHICK

NACA 66-021 AIRFOIL

Symmetric · 21% thick · low-to-mid Re
Compare↓ Download
PROFILENACA 66-021 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness21.0% @ 45%c
max camber0.0% @ 0%c
LE radius4.86%c
area upper / chord0.0702
area lower / chord-0.0702
area camber / chord0.0000
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.6771-5-0.11143.3330.454411.671.0220ClAngle 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 0.03818% of chord; maximum error 0.109%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
73.33
Angle at maximum lift / drag (°)
7
Minimum Cd
0.008072
Maximum Cl
0.8787
Angle at maximum Cl (°)
9
Cd at zero lift
0.008072
Cm at zero angle
6.08e-21
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…