Airfoil Data
GOE121
GOE 121 (MVA H.1) AIRFOIL
Wing Geometry Simulator
The GOE 121 (MVA H.1) AIRFOIL is a thin 7.5% chord-thickness airfoil with a maximum camber of 3.8% at 30% 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 -3.8°.
Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 56 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 GOE121 typically compare it against profiles of similar thickness: LWK 80-150/K25, EPPLER 330 AIRFOIL, GOE 403 AIRFOIL, MH 106 13.07%, WASP (smoothed). The NACA 66(3)-418 is another reference profile frequently considered alongside it.
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Engineers evaluating the GOE121 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (7.5%) and max camber (3.8%).
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