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NASA/LANGLEY RC10-64C AIRFOIL

Cambered · 10% thick · low-to-mid Re
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PROFILENASA/LANGLEY RC10-64C AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness10.0% @ 40%c
max camber1.0% @ 35%c
LE radius1.10%c
area upper / chord0.0423
area lower / chord-0.0298
area camber / chord0.0063
TE thickness0.20%c
DOWNLOAD COORDINATES

Polars

Preliminary
Combined estimate
-0.6003-50.18393.3330.968111.671.75220ClAngle of attack (°)
Why this curve

This curve combines the stored NeuralFoil prediction with 1 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 0.03753% of chord; maximum error 0.2323%.

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

  • · Converged

Curve summary

Combined estimate · Within -5° to 20°

Maximum lift / drag
145.3
Angle at maximum lift / drag (°)
9
Minimum Cd
0.005594
Maximum Cl
1.556
Angle at maximum Cl (°)
15
Cd at zero lift
0.005618
Cm at zero angle
-0.02836
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…