Airfoils.Pro
database / Aircraft and classic / CLARKYSM
AIRCRAFT AND CLASSICCAMBEREDSELIG-DATABASE

CLARKYSM

Cambered · 12% thick · low-to-mid Re
Compare↓ Download
PROFILECLARKYSM
surfacecamber line
GEOMETRY · AREA METRICS
max thickness11.7% @ 31%c
max camber3.6% @ 43%c
LE radius1.51%c
area upper / chord0.0645
area lower / chord-0.0166
area camber / chord0.0240
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
Combined estimate
-0.3012-50.31873.3330.938611.671.55920ClAngle 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 0.01264% of chord; maximum error 0.03795%.

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
84.04
Angle at maximum lift / drag (°)
6
Minimum Cd
0.01154
Maximum Cl
1.404
Angle at maximum Cl (°)
8
Cd at zero lift
0.01157
Cm at zero angle
-0.1007
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…