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NACA 64-008A AIRFOIL

Symmetric · 8% thick · low-to-mid Re
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PROFILENACA 64-008A AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness8.0% @ 39%c
max camber0.0% @ 0%c
LE radius0.70%c
area upper / chord0.0265
area lower / chord-0.0265
area camber / chord0.0000
TE thickness0.04%c
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Polars

Preliminary
Combined estimate
-0.7907-50.076543.3330.943711.671.81120ClAngle of attack (°)
Why this curve

This curve combines the stored NeuralFoil prediction with 0 contributing CFD observations. History windows remain observations, not separate solver runs or automatically converged points.

Model uncertainty is conditional on the stated assumptions and has not been calibrated for this condition. It is not a validated accuracy guarantee.

Geometry fit: RMS error 0.01663% of chord; maximum error 0.09408%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10 · Polar model progressive-polar-gp-v2

Curve summary

Combined estimate · Within -5° to 20°

Maximum lift / drag
111.4
Angle at maximum lift / drag (°)
9
Minimum Cd
0.006375
Maximum Cl
1.594
Angle at maximum Cl (°)
16
Cd at zero lift
0.006375
Cm at zero angle
6.863e-17
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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