Abstract
This paper presents the results of ground and wind-tunnel tests from the Piezoelectric Aeroelastic Response Tailoring Investigation. The key objectives of this research were to demonstrate active control of aeroelastic response at subcritical speeds (conditions below the wing flutter speed) and wing flutter suppression using a large-scale aeroelastic wind-tunnel model with distributed piezoelectric actuators. Experimental methodologies, challenges, and results are discussed. Active flutter suppression and reduced response at subcritical speeds using piezoelectric actuation was successfully demonstrated in NASA-Langley's Transonic Dynamics Tunnel. (Author)
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