Airfoil Data
NACA001066

The NACA 0010-66 is a thin 5.0% chord-thickness airfoil with a maximum camber of 2.5% at 60% 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 -2.5°.

Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 49 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 NACA001066 typically compare it against profiles of similar thickness: HQ 0/10 AIRFOIL, RAE 102 AIRFOIL, NACA 0010-64, NACA 0010-65, NASA SC(2)-0710 AIRFOIL. The NACA 0012-64 a=0.8 c(li)=0.2 is another reference profile frequently considered alongside it.