Airfoil Data
GOE770

The GOE 770 AIRFOIL is a 14.5% chord-thickness airfoil with a maximum camber of 7.3% at 30% 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 -7.3°.

Thin airfoil theory predicts a stall angle near 10.7° and a peak lift-to-drag ratio around 72 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 15% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

The GOE770 appears in the wing design of at least 3 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 GOE770 typically compare it against profiles of similar thickness: GW 19, GOE 503 AIRFOIL, GOE 592 AIRFOIL, GOE 514 AIRFOIL, AH 94-W-301. The GOE 393 AIRFOIL is another reference profile frequently considered alongside it.