Airfoil Data
E266
EPPLER 266 AIRFOIL
Wing Geometry Simulator
The EPPLER 266 AIRFOIL is a 11.9% chord-thickness airfoil with a maximum camber of 5.9% at 40% chord, suited to general-aviation and UAV wing design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -5.9°.
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 E266 appears in the wing design of at least 2 documented aircraft — notably by Schempp-Hirth. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the E266 typically compare it against profiles of similar thickness: NACA 2-H-15 AIRFOIL, FX S 03-182 AIRFOIL, FX 66-S-161 AIRFOIL, RAF 69 AIRFOIL, EPPLER 1200 AIRFOIL. The RAF 89 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the E266 Airfoil
Schempp-Hirth SH-1 | Schempp-Hirth | Eppler 266 | Constant |
Schempp-Hirth SHK | Schempp-Hirth | Eppler 266 | Constant |
Design wings in your spreadsheet
AeroSheet loads E266 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 E266 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (11.9%) and max camber (5.9%).
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