Airfoil Data
AS6091
AS6091 | Ananda-Selig | AIAA Paper 2018-0310
Wing Geometry Simulator
The AS6091 | Ananda-Selig | AIAA Paper 2018-0310 is a thin 6.0% chord-thickness airfoil with a maximum camber of 3.0% at 38% 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 AS6091 typically compare it against profiles of similar thickness: E226 (10.19%), RG-12, S1012, NASA SC(2)-0612 AIRFOIL, NASA SC(2)-0412 AIRFOIL. The GOE 503 AIRFOIL is another reference profile frequently considered alongside it.
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Engineers evaluating the AS6091 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (6.0%) and max camber (3.0%).
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