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CAMBEREDRESEARCHSELIG-DATABASETHIN

RAF 26 AIRFOIL

Cambered · 7% thick · low-to-mid Re
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PROFILERAF 26 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness6.6% @ 30%c
max camber2.1% @ 50%c
LE radius0.48%c
area upper / chord0.0366
area lower / chord-0.0083
area camber / chord0.0141
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
Combined estimate
-0.4345-50.093313.3330.621111.671.14920ClAngle of attack (°)
Why this curve

This curve combines the stored NeuralFoil prediction with 0 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 0.04415% of chord; maximum error 0.2052%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10 · Polar model progressive-polar-gp-v2

Curve summary

Combined estimate · Within -5° to 20°

Maximum lift / drag
131.4
Angle at maximum lift / drag (°)
5
Minimum Cd
0.005739
Maximum Cl
1.017
Angle at maximum Cl (°)
7
Cd at zero lift
0.005776
Cm at zero angle
-0.07409
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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