Airfoil Data
GOE767
GOE 767 AIRFOIL
Wing Geometry Simulator
The GOE 767 AIRFOIL is a thin 7.5% chord-thickness airfoil with a maximum camber of 3.8% 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 -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.
The GOE767 appears in the wing design of at least 1 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 GOE767 typically compare it against profiles of similar thickness: FX 71-L-150/30 AIRFOIL, NACA 16-015, E475 (15.01%), FX 71-L-150/30 AIRFOIL, D.G.A. 1138. The NACA 16-021 is another reference profile frequently considered alongside it.
Aircraft Using the GOE767 Airfoil
Schleicher Sperber Senior | Schleicher | Goettingen 757 | Goettingen 767 |
Wing lofting: 1 of these aircraft taper from GOE767 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 GOE767 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%).