Airfoil Data
GOE285

The GOE 285 AIRFOIL is a 9.6% chord-thickness airfoil with a maximum camber of 4.8% 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 -4.8°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 62 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 GOE285 appears in the wing design of at least 1 documented aircraft — notably by Cantieri. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the GOE285 typically compare it against profiles of similar thickness: GOE 167 (V.KARMAN PROP.2) AIRFOIL, EPPLER 637 AIRFOIL, RAF 6 AIRFOIL, FX 60-126/1 AIRFOIL, EPPLER 407 AIRFOIL. The NASA SC(2)-0714 AIRFOIL is another reference profile frequently considered alongside it.