Airfoil Data
FX77080
FX 77-080
Wing Geometry Simulator
The FX 77-080 is a thin 4.0% chord-thickness airfoil with a maximum camber of 2.0% at 28% 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 -2.0°.
Thin airfoil theory predicts a stall angle near 12.0° and a peak lift-to-drag ratio around 47 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 FX77080 typically compare it against profiles of similar thickness: NACA M2, LWK 80-080, NACA 63-206, NACA 0008, S9027 (8%). The GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL is another reference profile frequently considered alongside it.
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Engineers evaluating the FX77080 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (4.0%) and max camber (2.0%).
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