Airfoil Data
DS21

The DS21 Joe Wurts is a thin 6.0% chord-thickness airfoil with a maximum camber of 3.0% at 32% 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 DS21 typically compare it against profiles of similar thickness: NACA 63-210 AIRFOIL, NASA SC(2)-0612 AIRFOIL, LWK 80-120/K25, HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL, E226 (10.19%). The USA 35 A AIRFOIL is another reference profile frequently considered alongside it.