Airfoil Data
GOE571
GOE 571 AIRFOIL
Wing Geometry Simulator
The GOE 571 AIRFOIL is a thick 22.3% chord-thickness airfoil with a maximum camber of 11.2% at 29% chord, suited to high-lift UAV wings, RC sailplanes, and low-Reynolds-number slow-flyers. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -11.2°.
Thin airfoil theory predicts a stall angle near 8.0° and a peak lift-to-drag ratio around 81 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 22% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the GOE571 typically compare it against profiles of similar thickness: GOE 561 AIRFOIL, WORTMANN FX 77-W-343 AIRFOIL, KENNEDY AND MARSDEN AIRFOIL, Marsden, GOE 531 AIRFOIL. The E209 (13.72%) is another reference profile frequently considered alongside it.
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Engineers evaluating the GOE571 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (22.3%) and max camber (11.2%).
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