Airfoil Data
NACA65210

The NACA 65-210 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 NACA65210 appears in the wing design of at least 2 documented aircraft — notably by Lockheed. Its proven track record across rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the NACA65210 typically compare it against profiles of similar thickness: RAE(NPL) 5213 AIRFOIL, EPPLER 426 AIRFOIL, NACA 64-210, RG 14 9% AIRFOIL, GOE 344 (PFALZ 71) AIRFOIL. The NACA 64(3)-218 is another reference profile frequently considered alongside it.