Airfoil Data
GOE464

The GOE 464 AIRFOIL is a 12.2% chord-thickness airfoil with a maximum camber of 6.1% 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 -6.1°.

Thin airfoil theory predicts a stall angle near 11.5° 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.

Designers evaluating the GOE464 typically compare it against profiles of similar thickness: NACA 65(3)-618, GOE 645 AIRFOIL, WORTMANN FX 63-137 AIRFOIL, S1020 Ornithopter airfoil, GOE 615 AIRFOIL. The NASA SC(2)-0012 AIRFOIL is another reference profile frequently considered alongside it.