Airfoil Data
GOE624
GOE 624 AIRFOIL
Wing Geometry Simulator
The GOE 624 AIRFOIL is a 13.2% chord-thickness airfoil with a maximum camber of 6.6% at 30% chord, suited to high-lift UAV wings, RC sailplanes, and low-Reynolds-number slow-flyers. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -6.6°.
Thin airfoil theory predicts a stall angle near 11.2° and a peak lift-to-drag ratio around 70 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 13% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
The GOE624 appears in the wing design of at least 1 documented aircraft — notably by Team. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the GOE624 typically compare it against profiles of similar thickness: DOUGLAS LA203A AIRFOIL, WORTMANN FX 049-915 AIRFOIL, AH 93-W-257, WORTMANN FX 057-816, GOE 16K AIRFOIL. The GOE 401 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the GOE624 Airfoil
Team Aeroscepsy Gokuraku Tombo | Team | Goettingen 624 | Goettingen 535R |
Wing lofting: 1 of these aircraft taper from GOE624 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 GOE624 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (13.2%) and max camber (6.6%).