Airfoil Data
GOE389
GOE 389 AIRFOIL
Wing Geometry Simulator
The GOE 389 AIRFOIL is a 9.1% chord-thickness airfoil with a maximum camber of 4.5% 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 -4.5°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 61 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 GOE389 appears in the wing design of at least 1 documented aircraft — notably by Woodham. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the GOE389 typically compare it against profiles of similar thickness: S4158, CLARK W AIRFOIL, BOEING 737 ROOT AIRFOIL, MH 201 13.08%, EPPLER 636 AIRFOIL. The NACA M6 is another reference profile frequently considered alongside it.
Aircraft Using the GOE389 Airfoil
Woodham Super Camel | Woodham | Goettingen 535 | Goettingen 389 |
Wing lofting: 1 of these aircraft taper from GOE389 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 GOE389 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (9.1%) and max camber (4.5%).