Airfoil Data
GOE596

The GOE 596 AIRFOIL is a 8.8% chord-thickness airfoil with a maximum camber of 4.4% 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 -4.4°.

Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 60 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 GOE596 appears in the wing design of at least 3 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 GOE596 typically compare it against profiles of similar thickness: WORTMANN FX M2 AIRFOIL, RAF 32 MOD AIRFOIL, S2091-101-83, GOE 264 AIRFOIL, E392 (10.15%). The MH 26 10.99% is another reference profile frequently considered alongside it.