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The preliminary design of a wing with strain actuation and conventional flap actuation for vibration and flutter suppression experiments is completed. A two degree of freedom typical section model with steady aerodynamics is used to gain an understanding of the fundamentals of the strain actuated aeroelastic control problem. Actuation issues and the effects of fiber and geometric sweep are examined using the typical section. Controllers are designed using the Linear Quadratic Regulator (LQR) method and observers are designed using the Kalman filter. The results are verified through a series of parameter variations and the incorporation of unsteady aerodynamics. With the typical section analyses as a foundation, the actual design is begun. The functional requirements and the design parameters are explicitly outlined. Non-parametric studies are used to determine several of the geometric design parameters. Specifically, a scaling analysis is used to determine the piezoelectric thickness and th