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DAE-51 AIRFOIL

Cambered · 9% thick · low-to-mid Re
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PROFILEDAE-51 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness9.4% @ 30%c
max camber4.0% @ 45%c
LE radius0.97%c
area upper / chord0.0583
area lower / chord-0.0038
area camber / chord0.0272
TE thickness0.20%c
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Polars

Preliminary
NeuralFoil
-0.267-50.343.3330.947111.671.55420ClAngle 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 0.01119% of chord; maximum error 0.07882%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
157.6
Angle at maximum lift / drag (°)
6
Minimum Cd
0.006156
Maximum Cl
1.402
Angle at maximum Cl (°)
7
Cd at zero lift
0.006299
Cm at zero angle
-0.1165
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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