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AIRCRAFT AND CLASSICCAMBEREDSELIG-DATABASETHICK

DAVIS_CORRECTED

Cambered · 16% thick · low-to-mid Re
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PROFILEDAVIS_CORRECTED
surfacecamber line
GEOMETRY · AREA METRICS
max thickness15.9% @ 29%c
max camber2.5% @ 30%c
LE radius2.79%c
area upper / chord0.0644
area lower / chord-0.0370
area camber / chord0.0137
TE thickness0.00%c
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Polars

Preliminary
NeuralFoil
-0.5969-50.20213.3331.00111.671.820ClAngle 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.

Geometry fit: RMS error 0.01278% of chord; maximum error 0.04274%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
119.6
Angle at maximum lift / drag (°)
11
Minimum Cd
0.007656
Maximum Cl
1.601
Angle at maximum Cl (°)
16
Cd at zero lift
0.007668
Cm at zero angle
-0.01788
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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