Airfoil Data
GOE612

The GOE 612 AIRFOIL is a 12.1% chord-thickness airfoil with a maximum camber of 6.0% at 39% chord, suited to high-lift UAV wings, RC sailplanes, and low-Reynolds-number slow-flyers. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -6.0°.

Thin airfoil theory predicts a stall angle near 11.6° and a peak lift-to-drag ratio around 69 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 12% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

The GOE612 appears in the wing design of at least 1 documented aircraft — notably by Cantieri. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the GOE612 typically compare it against profiles of similar thickness: GOE 621 AIRFOIL, EPPLER 399 AIRFOIL, S1210 12%, WORTMANN FX 05-191 AIRFOIL, NACA 63(3)-618. The GIII BL145 AIRFOIL is another reference profile frequently considered alongside it.