Airfoil Data
GOE600
GOE 600 AIRFOIL
Wing Geometry Simulator
The GOE 600 AIRFOIL is a 8.3% chord-thickness airfoil with a maximum camber of 4.1% at 39% 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 GOE600 appears in the wing design of at least 3 documented aircraft, including designs from Heinkel and Fieseler. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the GOE600 typically compare it against profiles of similar thickness: GOE 376 AIRFOIL, E387, S1014, GOE 269 AIRFOIL, GOE 677 (= M 6) AIRFOIL. The GOE 483 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the GOE600 Airfoil
Fieseler Fi 167 | Fieseler | Goettingen 600? | Constant |
Heinkel He 64 | Heinkel | Goettingen 600 ? | Constant |
Heinkel He 70 Blitz | Heinkel | Goettingen 600 (13%) | Goettingen 600 (10.2%) |
Wing lofting: 1 of these aircraft taper from GOE600 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 GOE600 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%).