Airfoil Data
NACA66210

The NACA 66-210 is a thin 6.1% chord-thickness airfoil with a maximum camber of 3.0% at 45% 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.

Designers evaluating the NACA66210 typically compare it against profiles of similar thickness: S2048, GIII BL0 AIRFOIL, GOE 344 (PFALZ 71) AIRFOIL, NACA 65-210, (Dicke 12.28%). The NACA 64-008A AIRFOIL is another reference profile frequently considered alongside it.