Airfoils.Pro
database / NACA 6-series / NACA 64A-010 10.0%
NACA 6-SERIESSELIG-DATABASESYMMETRIC

NACA 64A-010 10.0%

Symmetric · 10% thick · low-to-mid Re
Compare↓ Download
PROFILENACA 64A-010 10.0%
surfacecamber line
GEOMETRY · AREA METRICS
max thickness10.0% @ 39%c
max camber0.0% @ 0%c
LE radius1.10%c
area upper / chord0.0331
area lower / chord-0.0331
area camber / chord0.0000
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.7884-50.089063.3330.966611.671.84420ClAngle 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 0.01391% of chord; maximum error 0.03633%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
116.6
Angle at maximum lift / drag (°)
10
Minimum Cd
0.006704
Maximum Cl
1.625
Angle at maximum Cl (°)
16
Cd at zero lift
0.006704
Cm at zero angle
1.716e-17
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…