Airfoil Data
GOE676
GOE 676 (= M 12) AIRFOIL
Wing Geometry Simulator
The GOE 676 (= M 12) AIRFOIL is a thin 8.0% chord-thickness airfoil with a maximum camber of 4.0% 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 -4.0°.
Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 58 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 GOE676 appears in the wing design of at least 19 documented aircraft, including designs from Arsenal and DFS. 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 GOE676 typically compare it against profiles of similar thickness: GOE 457 AIRFOIL, NACA M14 AIRFOIL, NACA M12 AIRFOIL, OAF102 AIRFOIL, GOE 278 (DAIMLER IX) AIRFOIL. The GOE 456 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the GOE676 Airfoil
Wing lofting: 18 of these aircraft taper from GOE676 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 GOE676 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (8.0%) and max camber (4.0%).