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RAF 19 AIRFOIL

Cambered · 10% thick · low-to-mid Re
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PROFILERAF 19 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness10.5% @ 15%c
max camber10.1% @ 39%c
LE radius1.21%c
area upper / chord0.0959
area lower / chord0.0351
area camber / chord0.0655
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
Combined estimate
0.1083-50.70513.3331.30211.671.89920ClAngle 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 0.09269% of chord; maximum error 0.3245%.

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
154.8
Angle at maximum lift / drag (°)
5
Minimum Cd
0.007683
Maximum Cl
1.75
Angle at maximum Cl (°)
9
Cd at zero lift
—
Cm at zero angle
-0.1747
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…