Airfoils.Pro
database / NACA 6-series / NACA 63(2)-615
CAMBEREDNACA 6-SERIESSELIG-DATABASE

NACA 63(2)-615

Cambered · 15% thick · low-to-mid Re
Compare↓ Download
PROFILENACA 63(2)-615
surfacecamber line
GEOMETRY · AREA METRICS
max thickness15.0% @ 35%c
max camber3.3% @ 50%c
LE radius2.48%c
area upper / chord0.0710
area lower / chord-0.0227
area camber / chord0.0242
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.2142-50.39023.3330.994611.671.59920ClAngle 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 0.03361% of chord; maximum error 0.1221%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
146.5
Angle at maximum lift / drag (°)
5
Minimum Cd
0.006708
Maximum Cl
1.448
Angle at maximum Cl (°)
7
Cd at zero lift
0.006742
Cm at zero angle
-0.1366
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…