Airfoils.Pro
database / NACA 6-series / NACA 66(2)-215
CAMBEREDNACA 6-SERIESSELIG-DATABASE

NACA 66(2)-215

Cambered · 15% thick · low-to-mid Re
Compare↓ Download
PROFILENACA 66(2)-215
surfacecamber line
GEOMETRY · AREA METRICS
max thickness15.0% @ 45%c
max camber1.1% @ 50%c
LE radius2.48%c
area upper / chord0.0588
area lower / chord-0.0427
area camber / chord0.0081
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.6027-50.19243.3330.987511.671.78320ClAngle 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 0.03154% of chord; maximum error 0.1167%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
114.1
Angle at maximum lift / drag (°)
9
Minimum Cd
0.007628
Maximum Cl
1.584
Angle at maximum Cl (°)
17
Cd at zero lift
0.007636
Cm at zero angle
-0.03978
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…