Airfoil Data
PRANDTL-D-WINGTIP
Prandtl-D Wingtip NASA TP-2016-219072
Wing Geometry Simulator
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.
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Related Airfoils
Engineers evaluating the PRANDTL-D-WINGTIP frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (4.8%) and max camber (2.4%).
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