Airfoil Data
GOE409
GOE 409 AIRFOIL
Wing Geometry Simulator
The GOE 409 AIRFOIL is a thin 6.3% chord-thickness airfoil with a maximum camber of 3.2% 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 -3.2°.
Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 53 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 GOE409 appears in the wing design of at least 2 documented aircraft — notably by Schleicher. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the GOE409 typically compare it against profiles of similar thickness: GOE 459 AIRFOIL, GOE 599 AIRFOIL, S7012 8.75%, GOE 622 AIRFOIL, MH 44 9.66%. The ONERA OA206 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the GOE409 Airfoil
Schleicher Rhonsperber | Schleicher | Goettingen 535 | Goettingen 409 |
Schleicher Sperber Junior | Schleicher | Goettingen 535 | Goettingen 409 |
Wing lofting: 2 of these aircraft taper from GOE409 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 GOE409 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (6.3%) and max camber (3.2%).