Airfoil Data
GOE655

The GOE 655 AIRFOIL is a 11.3% chord-thickness airfoil with a maximum camber of 5.6% 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 -5.6°.

Thin airfoil theory predicts a stall angle near 11.6° and a peak lift-to-drag ratio around 67 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 11% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

The GOE655 appears in the wing design of at least 1 documented aircraft — notably by Messerschmitt. Its proven track record across rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the GOE655 typically compare it against profiles of similar thickness: N-10, N-11, DAI 1238, FX 84-W-140, FX 63-145 AIRFOIL. The Prandtl-D Wingtip NASA TP-2016-219072 is another reference profile frequently considered alongside it.