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RAE6-9CK AIRFOIL

Cambered · 12% thick · low-to-mid Re
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PROFILERAE6-9CK AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness12.1% @ 38%c
max camber1.3% @ 76%c
LE radius1.61%c
area upper / chord0.0442
area lower / chord-0.0337
area camber / chord0.0053
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
Combined estimate
-0.5467-50.3173.3331.18111.672.04420ClAngle 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 0.005052% of chord; maximum error 0.01705%.

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
114.1
Angle at maximum lift / drag (°)
10
Minimum Cd
0.008208
Maximum Cl
1.829
Angle at maximum Cl (°)
16
Cd at zero lift
0.008222
Cm at zero angle
-0.07577
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…