Airfoil Data
E560

The EPPLER 560 AIRFOIL is a 12.1% chord-thickness airfoil with a maximum camber of 6.0% at 32% 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 E560 appears in the wing design of at least 1 documented aircraft — notably by Geneva. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the E560 typically compare it against profiles of similar thickness: GOE 626 AIRFOIL, NACA 63(3)-618, S1210 12%, WORTMANN FX 05-191 AIRFOIL, EPPLER 399 AIRFOIL. The NASA SC(2)-0414 AIRFOIL is another reference profile frequently considered alongside it.