Airfoil Data
E662
EPPLER E662 AIRFOIL
Wing Geometry Simulator
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.
Aircraft Using the E662 Airfoil
Grob 104 Speed Astir II | Grob | Eppler 662 | Constant |
Grob 104 Speed Astir IIB | Grob | Eppler 662 | Constant |
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Engineers evaluating the E662 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (11.6%) and max camber (5.8%).
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