Airfoil Data
GOE601

The GOE 601 AIRFOIL is a 10.2% chord-thickness airfoil with a maximum camber of 5.1% at 39% 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 -5.1°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 64 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 10% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

The GOE601 appears in the wing design of at least 1 documented aircraft — notably by Junkers. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the GOE601 typically compare it against profiles of similar thickness: GOE 460 AIRFOIL, GOE 575 AIRFOIL, EPPLER 329 AIRFOIL, EPPLER 542 AIRFOIL, SG6043. The MH 150 23.89% is another reference profile frequently considered alongside it.