Airfoil Data
GOE677
GOE 677 (= M 6) AIRFOIL
Wing Geometry Simulator
The GOE 677 (= M 6) AIRFOIL is a 8.3% chord-thickness airfoil with a maximum camber of 4.1% at 30% chord, suited to general-aviation and UAV wing design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -4.1°.
Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 59 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 GOE677 appears in the wing design of at least 1 documented aircraft — notably by Mitsubishi. Its proven track record across rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the GOE677 typically compare it against profiles of similar thickness: S1014, GOE 376 AIRFOIL, GOE 133 (MVA H.11) AIRFOIL, GOE 600 AIRFOIL, E387. The MH 113 14.62% is another reference profile frequently considered alongside it.
Aircraft Using the GOE677 Airfoil
Mitsubishi Ki-1 | Mitsubishi | Goettingen 677 ? | Goettingen ? |
Wing lofting: 1 of these aircraft taper from GOE677 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 GOE677 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (8.3%) and max camber (4.1%).