Airfoil Data
NACA63A210

The NACA 63A210 is a thin 6.2% chord-thickness airfoil with a maximum camber of 3.1% at 40% 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 -3.1°.

Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 53 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 NACA63A210 appears in the wing design of at least 1 documented aircraft — notably by Tecnam. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the NACA63A210 typically compare it against profiles of similar thickness: MH 62 9.3%, AS6092 | Ananda-Selig | AIAA Paper 2018-0310, AG24 Bubble Dancer DLG by Mark Drela | The AG2x airfoils are intended to be used on composite versions of the Bubble Dancer and the Allegro-Lite., EPPLER E851 AIRFOIL, S6061 9%. The NACA 16-012 is another reference profile frequently considered alongside it.