Airfoil Data
E662

The EPPLER E662 AIRFOIL is a 11.6% chord-thickness airfoil with a maximum camber of 5.8% at 43% 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 -5.8°.

Thin airfoil theory predicts a stall angle near 11.6° and a peak lift-to-drag ratio around 68 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 E662 appears in the wing design of at least 2 documented aircraft — notably by Grob. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the E662 typically compare it against profiles of similar thickness: NACA 65(4)-221, AH 93-156, AH 93-157, GOE 404 AIRFOIL, EPPLER 585 AIRFOIL. The E385 (8.41%) is another reference profile frequently considered alongside it.