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RAF 6 AIRFOIL

Cambered · 10% thick · low-to-mid Re
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PROFILERAF 6 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness10.0% @ 30%c
max camber4.6% @ 30%c
LE radius1.10%c
area upper / chord0.0702
area lower / chord-0.0032
area camber / chord0.0335
TE thickness0.30%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.1018-50.52833.3331.15811.671.78920ClAngle 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 0.1143% of chord; maximum error 0.36%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
159.4
Angle at maximum lift / drag (°)
6
Minimum Cd
0.006691
Maximum Cl
1.631
Angle at maximum Cl (°)
9
Cd at zero lift
—
Cm at zero angle
-0.1308
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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