This paper presents the results of wind tunnel testing performed on a three-dimensional adaptive wing structure. The focus of this study was to test the aeroelastic response and control of a wing built with adaptive stressed skins. The aeroelastic performance of the wing using traditional aerodynamic control surface methods is compared to the results obtained using piezoelectric actuators bonded to the skins of the wing. Smaller piezoelectric sensors also bonded to the wing are used to provide feedback for the control law. Results are presented for the system identification, free stream vibration and buffeting tests performed in the wind tunnel.
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