Airfoil Data
N63212

The NACA 63-212 AIRFOIL is a thin 7.0% chord-thickness airfoil with a maximum camber of 3.5% at 35% chord, suited to high-speed UAVs, sailplane tip sections, and propeller blade design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -3.5°.

Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 55 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The slim profile minimises pressure drag at higher speeds but leaves limited spar depth for structural integration.

The N63212 appears in the wing design of at least 11 documented aircraft, including designs from FMA and DaeWoo. 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 N63212 typically compare it against profiles of similar thickness: LOCKHEED C-141 BL761.11 AIRFOIL, ESA40, NASA SC(2)-0414 AIRFOIL, SD6060-104-88, GOE 377 AIRFOIL. The NACA 64(4)-221 is another reference profile frequently considered alongside it.