Airfoil Data
GOE593

The GOE 593 AIRFOIL is a 9.9% chord-thickness airfoil with a maximum camber of 5.0% at 40% 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 -5.0°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 63 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 GOE593 appears in the wing design of at least 5 documented aircraft, including designs from Curtiss-Wright and Day. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the GOE593 typically compare it against profiles of similar thickness: DORNIER A-5 AIRFOIL, MB253515 15.0% smoothed, GEMINI (smoothed), LISSAMAN 7769 AIRFOIL, GOE 746 AIRFOIL. The FX 69-274 is another reference profile frequently considered alongside it.