Airfoil Data
NACA64A210

The NACA 64A210 is a thin 6.3% 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 NACA64A210 appears in the wing design of at least 9 documented aircraft, including designs from Panstwowe and Bushby. 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 NACA64A210 typically compare it against profiles of similar thickness: RAE6-9CK AIRFOIL, RAE 2822 AIRFOIL, NACA 0010-34 a=0.8 c(li)=0.2, KC-135 Winglet (supercritical Whitcomb), BOEING 707 .99 SPAN AIRFOIL. The NACA M23 AIRFOIL is another reference profile frequently considered alongside it.