Airfoil Data
GOE55
GOE 55 AIRFOIL
Wing Geometry Simulator
The GOE 55 AIRFOIL is a thin 5.1% chord-thickness airfoil with a maximum camber of 2.5% at 20% 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 -2.5°.
Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 50 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 GOE55 typically compare it against profiles of similar thickness: NASA/LANGLEY RC-08(B)3 AIRFOIL, Supermarine 371-II (tip), EPPLER E850 AIRFOIL, AG03 (flat aft bottom), BOEING 707 .08 SPAN AIRFOIL. The Apex 16 (normalized using XFOIL date021206) is another reference profile frequently considered alongside it.
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Engineers evaluating the GOE55 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (5.1%) and max camber (2.5%).
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