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CAMBEREDNACA 5-DIGITSELIG-DATABASE

NACA 64-110 AIRFOIL

Cambered · 10% thick · low-to-mid Re
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PROFILENACA 64-110 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness10.0% @ 39%c
max camber0.6% @ 50%c
LE radius1.10%c
area upper / chord0.0357
area lower / chord-0.0277
area camber / chord0.0040
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.7193-50.17283.3331.06511.671.95720ClAngle 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 0.02196% of chord; maximum error 0.1044%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
124.8
Angle at maximum lift / drag (°)
10
Minimum Cd
0.006586
Maximum Cl
1.734
Angle at maximum Cl (°)
16
Cd at zero lift
0.00659
Cm at zero angle
-0.02141
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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