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USA 22 AIRFOIL

Cambered · 9% thick · low-to-mid Re
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PROFILEUSA 22 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness9.1% @ 20%c
max camber4.4% @ 39%c
LE radius0.91%c
area upper / chord0.0566
area lower / chord-0.0002
area camber / chord0.0282
TE thickness0.10%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.3185-50.3733.3331.06411.671.75620ClAngle 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 0.05302% of chord; maximum error 0.2716%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
158.3
Angle at maximum lift / drag (°)
7
Minimum Cd
0.006091
Maximum Cl
1.583
Angle at maximum Cl (°)
9
Cd at zero lift
0.006148
Cm at zero angle
-0.0897
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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