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CAMBEREDRESEARCHSELIG-DATABASETHICK

RAF 89 AIRFOIL

Cambered · 25% thick · low-to-mid Re
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PROFILERAF 89 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness25.0% @ 30%c
max camber1.6% @ 50%c
LE radius6.88%c
area upper / chord0.0928
area lower / chord-0.0714
area camber / chord0.0107
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.538-50.10733.3330.752611.671.39820ClAngle 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 0.154% of chord; maximum error 0.6066%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
54.98
Angle at maximum lift / drag (°)
8
Minimum Cd
0.00985
Maximum Cl
1.237
Angle at maximum Cl (°)
20
Cd at zero lift
0.009851
Cm at zero angle
-0.02858
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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