Airfoil Data
GOE550

The GOE 550 AIRFOIL is a 10.1% 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 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 GOE550 appears in the wing design of at least 2 documented aircraft — notably by Doppelraab. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the GOE550 typically compare it against profiles of similar thickness: MRC-16, EPPLER 598 AIRFOIL, GOE 574 AIRFOIL, NACA 65(3)-218, GOE 7K AIRFOIL. The EPPLER 338 AIRFOIL is another reference profile frequently considered alongside it.