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AIRCRAFT AND CLASSICCAMBEREDSELIG-DATABASE

CLARK YS AIRFOIL

Cambered · 12% thick · low-to-mid Re
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PROFILECLARK YS AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness11.7% @ 30%c
max camber2.3% @ 30%c
LE radius1.51%c
area upper / chord0.0503
area lower / chord-0.0301
area camber / chord0.0101
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.756-5-0.082873.3330.590311.671.26320ClAngle 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.

The compressibility correction is a low-fidelity estimate, not a resolved shock or compressible CFD solution.

Geometry fit: RMS error 0.0696% of chord; maximum error 0.3442%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
117.4
Angle at maximum lift / drag (°)
8
Minimum Cd
0.006536
Maximum Cl
1.095
Angle at maximum Cl (°)
9
Cd at zero lift
0.006572
Cm at zero angle
0.03044
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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