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USA 51 AIRFOIL

Cambered · 9% thick · low-to-mid Re
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PROFILEUSA 51 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness9.3% @ 30%c
max camber2.6% @ 30%c
LE radius0.96%c
area upper / chord0.0483
area lower / chord-0.0145
area camber / chord0.0169
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.4776-50.15913.3330.795811.671.43320ClAngle 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 0.05633% of chord; maximum error 0.2943%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
140.9
Angle at maximum lift / drag (°)
7
Minimum Cd
0.006134
Maximum Cl
1.273
Angle at maximum Cl (°)
9
Cd at zero lift
0.006154
Cm at zero angle
-0.05136
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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