AF—01
AeroForge / aerodynamic design studio
NACA 2412
/
Design. Simulate. Optimize.
Model status
Loading model
Domain status
In domain
Inference ms
—
Loading model
Section study / finite trailing edge
Chord c = 1.000
Airfoil at 4 degrees
Accurate NACA upper and lower surfaces with equal horizontal and vertical scale. Positive angle rotates the leading edge upward. Drag the handles to edit geometry or incidence.
LEADING EDGE
x/c 0.000
TRAILING EDGE
FINITE GAP
MAX CAMBER
2.0% / 40%c
MAX THICKNESS
12.0%c / x/c 0.300
REFERENCE CHORD
c = 1.000
Drag handles / shift + arrows for coarse
Reset view
Section geometry / live study
NACA 2412
Alpha 4.0° / Re 250k /
In domain
Presets
0012
2412
4412
More
Save design
▶
Alpha sweep
4.0°
Space / play-pause
-4°
0°
4°
8°
12°
Charts +
Export +
Reset
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2D / equal axis scale