Airfoils.Pro
database / Aircraft and classic / USA 34 AIRFOIL
AIRCRAFT AND CLASSICCAMBEREDSELIG-DATABASETHICK

USA 34 AIRFOIL

Cambered · 18% thick · low-to-mid Re
Compare↓ Download
PROFILEUSA 34 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness18.0% @ 29%c
max camber7.7% @ 39%c
LE radius3.58%c
area upper / chord0.1130
area lower / chord-0.0116
area camber / chord0.0507
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.06175-50.54073.3331.14311.671.74620ClAngle 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 0.07104% of chord; maximum error 0.2954%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
69.56
Angle at maximum lift / drag (°)
6
Minimum Cd
0.008873
Maximum Cl
1.595
Angle at maximum Cl (°)
13
Cd at zero lift
—
Cm at zero angle
-0.08585
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…