Airfoil Data
NACA6412
NACA 6412
Wing Geometry Simulator
The NACA 6412 is a 11.8% chord-thickness airfoil with a maximum camber of 5.9% at 34% chord, suited to general-aviation and UAV wing design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -5.9°.
Thin airfoil theory predicts a stall angle near 11.6° and a peak lift-to-drag ratio around 69 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 12% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
The NACA6412 appears in the wing design of at least 6 documented aircraft, including designs from Avia and Breguet. Its proven track record across conventional and rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the NACA6412 typically compare it against profiles of similar thickness: FX S 03-182 AIRFOIL, EPPLER 266 AIRFOIL, NACA 2-H-15 AIRFOIL, FX 66-S-161 AIRFOIL, AH 83-159. The GOE 735 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the NACA6412 Airfoil
Avia Baltika LAK-X | Avia | NACA 64-?15 | NACA 64-?12 |
Breguet 1150 Atlantique | Breguet | NACA 64-?16 | NACA 64-?12 |
Dassault Atlantique 2 | Dassault | NACA 64-?16 | NACA 64-?12 |
Polyteknisk Flyvegruppe Polyt 3B | Polyteknisk | Clark Y (15.7%) | NACA 6412 |
Slingsby T.49 Capstan | Slingsby | NACA 63-620 | NACA 6412 |
Bell 301 XV-15 (original blades) | Bell | NACA 64-935/528/118 | NACA 64-(1.5)12/208 |
Wing lofting: 6 of these aircraft taper from NACA6412 at the root to a different tip section. Use the Tapered filter to isolate them, then click any tip airfoil link to compare geometries.
Related Airfoils
Engineers evaluating the NACA6412 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (11.8%) and max camber (5.9%).