Airfoil Data
GOE585

The GOE 585 AIRFOIL is a thin 7.3% chord-thickness airfoil with a maximum camber of 3.6% 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 -3.6°.

Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 56 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 GOE585 appears in the wing design of at least 1 documented aircraft — notably by Dornier. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the GOE585 typically compare it against profiles of similar thickness: GOE 372 AIRFOIL, SD2083 (9.0%), RAE(NPL) 5212 AIRFOIL, S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane), RG 15A-1.8/11.0 AIRFOIL. The NACA 65(2)-415 a=0.5 is another reference profile frequently considered alongside it.