Airfoil Data
GOE565
GOE 565 AIRFOIL
Wing Geometry Simulator
The GOE 565 AIRFOIL is a thin 6.8% chord-thickness airfoil with a maximum camber of 3.4% at 40% 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 -3.4°.
Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 54 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.
The GOE565 appears in the wing design of at least 2 documented aircraft, including designs from Junkers and Mitsubishi. Its proven track record across conventional and rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the GOE565 typically compare it against profiles of similar thickness: BOEING 737 OUTBOARD AIRFOIL, St. CYR 172 (Royer), S3016-095-87, S9000 (9%), LOCKHEED C-5A BL758.6 AIRFOIL. The FX 84-W-097 is another reference profile frequently considered alongside it.
Aircraft Using the GOE565 Airfoil
Junkers G38 | Junkers | Goettingen 290 ? | Goettingen 565 ? |
Mitsubishi Ki-20 | Mitsubishi | Goettingen 290 ? | Goettingen 565 ? |
Wing lofting: 2 of these aircraft taper from GOE565 at the root to a different tip section. Use the Tapered filter to isolate them, then click any tip airfoil link to compare geometries.
Related Airfoils
Engineers evaluating the GOE565 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (6.8%) and max camber (3.4%).