Abstract
Experimental buffeting and gust alleviation response results are presented for a sweptback flat wing model using piezoelectric actuators to control bending and wing tip camber shape. Model response was sensed by a small piezoceramic wafer mounted at the root. Two actuation strategies were implemented: the traditional actuators mounted at the root were used to provide structural damping, and a shape control mechanism using a pair of actuators near the wing tip were used to change the airfoil camber shape. Results obtained from wind-tunnel tests of the wing model are presented for the open- and closed-loop systems. The results of this experimental study show that piezoelectric actuation is effective in attenuating vibration and the wake-induced buffet response over the range of parameters investigated. Also, the airfoil camber shape control increases remarkably the efficiency of the system, by using a controlled change of lift in order to produce the required bending moments.
