Airfoil Data
NACA64210

The NACA 64-210 is a thin 6.1% chord-thickness airfoil with a maximum camber of 3.0% 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 -3.0°.

Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 52 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 NACA64210 appears in the wing design of at least 13 documented aircraft, including designs from AerMacchi and Ambrosini. 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 NACA64210 typically compare it against profiles of similar thickness: EPPLER 426 AIRFOIL, RAE(NPL) 5213 AIRFOIL, RG 14 9% AIRFOIL, AH 85-L-120/17, NACA 65-210. The NACA 63-206 is another reference profile frequently considered alongside it.