Airfoil Data
PRANDTL-D-WINGTIP

The Prandtl-D Wingtip NASA TP-2016-219072 is a thin 4.8% chord-thickness airfoil with a maximum camber of 2.4% at 27% 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 -2.4°.

Thin airfoil theory predicts a stall angle near 12.0° 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 PRANDTL-D-WINGTIP typically compare it against profiles of similar thickness: AG04, AG18, S6063 7.05%, BELL 540 AIRFOIL (MODIFIED NACA 0012), EPPLER 874 HYDROFOIL AIRFOIL. The S1091 is another reference profile frequently considered alongside it.