Airfoil Data
DU861372
DU 86-137/25 AIRFOIL
Wing Geometry Simulator
The DU 86-137/25 AIRFOIL is a thin 6.8% chord-thickness airfoil with a maximum camber of 3.4% at 42% 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 -3.4°.
Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 54 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 DU861372 typically compare it against profiles of similar thickness: SIKORSKY SC1094 R8 AIRFOIL, LOCKHEED C-5A BL576 AIRFOIL, GOE 100 (SOPWITH) AIRFOIL, E71 (5.15%), SD7090 (10%). The NASA SC(2)-0706 AIRFOIL is another reference profile frequently considered alongside it.
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Related Airfoils
Engineers evaluating the DU861372 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (6.8%) and max camber (3.4%).
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