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AIRCRAFT AND CLASSICCAMBEREDSELIG-DATABASE

DAE 41

Cambered · 12% thick · low-to-mid Re
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PROFILEDAE 41
surfacecamber line
GEOMETRY · AREA METRICS
max thickness11.7% @ 31%c
max camber3.0% @ 41%c
LE radius1.50%c
area upper / chord0.0582
area lower / chord-0.0179
area camber / chord0.0202
TE thickness0.00%c
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Polars

Preliminary
NeuralFoil
-0.4402-50.16923.3330.778711.671.38820ClAngle 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 0.01038% of chord; maximum error 0.04537%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
141.3
Angle at maximum lift / drag (°)
6
Minimum Cd
0.006327
Maximum Cl
1.236
Angle at maximum Cl (°)
7
Cd at zero lift
0.006328
Cm at zero angle
-0.06883
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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