Airfoil Data
E560
EPPLER 560 AIRFOIL
Wing Geometry Simulator
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.
Aircraft Using the E560 Airfoil
Geneva Aerospace Dakota | Geneva | Eppler 560 | Constant |
Design wings in your spreadsheet
AeroSheet loads E560 airfoils directly into Google Sheets. Polars, 3D splines, Fusion 360 export, without leaving your spreadsheet.
Install in Google Sheets coming soonRelated Airfoils
Engineers evaluating the E560 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (12.1%) and max camber (6.0%).
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