Airfoils.Pro
database / Aircraft and classic / USA-35B AIRFOIL
AIRCRAFT AND CLASSICCAMBEREDSELIG-DATABASE

USA-35B AIRFOIL

Cambered · 12% thick · low-to-mid Re
Compare↓ Download
PROFILEUSA-35B AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness11.6% @ 30%c
max camber3.2% @ 30%c
LE radius1.48%c
area upper / chord0.0530
area lower / chord-0.0248
area camber / chord0.0141
TE thickness0.25%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.07868-50.48373.3331.04611.671.60820ClAngle 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 0.06031% of chord; maximum error 0.2982%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
138.8
Angle at maximum lift / drag (°)
5
Minimum Cd
0.007208
Maximum Cl
1.468
Angle at maximum Cl (°)
7
Cd at zero lift
—
Cm at zero angle
-0.1022
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…