Airfoils.Pro
database / Aircraft and classic / CLARK V AIRFOIL
AIRCRAFT AND CLASSICCAMBEREDSELIG-DATABASE

CLARK V AIRFOIL

Cambered · 12% thick · low-to-mid Re
Compare↓ Download
PROFILECLARK V AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness11.6% @ 30%c
max camber3.4% @ 50%c
LE radius1.49%c
area upper / chord0.0651
area lower / chord-0.0177
area camber / chord0.0237
TE thickness0.14%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.3049-50.31713.3330.939111.671.56120ClAngle 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 0.05561% of chord; maximum error 0.2765%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
146.4
Angle at maximum lift / drag (°)
6
Minimum Cd
0.006572
Maximum Cl
1.406
Angle at maximum Cl (°)
8
Cd at zero lift
0.006573
Cm at zero angle
-0.1105
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…