Airfoil Data
NACA63209

The NACA 63-209 is a thin 5.5% chord-thickness airfoil with a maximum camber of 2.8% at 35% 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 -2.8°.

Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 51 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 NACA63209 typically compare it against profiles of similar thickness: DSMA-523B AIRFOIL, DSMA-523A AIRFOIL, NACA 64-110 AIRFOIL, AG44ct -02f, St. CYR 171 (Royer). The NACA 66(2)-415 is another reference profile frequently considered alongside it.