Airfoil Data
E664
EPPLER 664 AIRFOIL
Wing Geometry Simulator
The EPPLER 664 AIRFOIL is a 11.1% chord-thickness airfoil with a maximum camber of 5.5% at 41% 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 -5.5°.
Thin airfoil theory predicts a stall angle near 11.6° and a peak lift-to-drag ratio around 66 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 11% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the E664 typically compare it against profiles of similar thickness: EPPLER 664 (EXTENDED) AIRFOIL, FX 60-177 AIRFOIL, FX 83-W-160, NACA 63,3-418, SM701. The AH 88-K-136/16 is another reference profile frequently considered alongside it.
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Related Airfoils
Engineers evaluating the E664 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (11.1%) and max camber (5.5%).
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