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NACA 5-DIGITSELIG-DATABASESYMMETRIC

NACA 64-012A AIRFOIL

Symmetric · 12% thick · low-to-mid Re
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PROFILENACA 64-012A AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness12.0% @ 39%c
max camber0.0% @ 0%c
LE radius1.58%c
area upper / chord0.0395
area lower / chord-0.0395
area camber / chord0.0000
TE thickness0.05%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.8008-50.086163.3330.973211.671.8620ClAngle 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 0.02062% of chord; maximum error 0.1055%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
118.6
Angle at maximum lift / drag (°)
11
Minimum Cd
0.007014
Maximum Cl
1.638
Angle at maximum Cl (°)
16
Cd at zero lift
0.007014
Cm at zero angle
-3.432e-17
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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