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CAMBEREDNACA 5-DIGITSELIG-DATABASE

NACA 63-210 AIRFOIL

Cambered · 10% thick · low-to-mid Re
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PROFILENACA 63-210 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness10.0% @ 35%c
max camber1.1% @ 59%c
LE radius1.10%c
area upper / chord0.0396
area lower / chord-0.0235
area camber / chord0.0080
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
Combined estimate
-0.6212-50.26033.3331.14211.672.02320ClAngle 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 0.02484% of chord; maximum error 0.1143%.

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
131.2
Angle at maximum lift / drag (°)
9
Minimum Cd
0.006585
Maximum Cl
1.803
Angle at maximum Cl (°)
16
Cd at zero lift
0.006594
Cm at zero angle
-0.04395
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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