Airfoil Data
GOE570

The GOE 570 AIRFOIL is a thick 26.4% chord-thickness airfoil with a maximum camber of 13.2% 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 -13.2°.

Thin airfoil theory predicts a stall angle near 8.0° and a peak lift-to-drag ratio around 86 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 26% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the GOE570 typically compare it against profiles of similar thickness: FX 79-W-470A, AH 93-W-480B, Marsden, GOE 561 AIRFOIL, GOE 571 AIRFOIL. The NACA 63(2)-615 is another reference profile frequently considered alongside it.