Reduced-order models of potential-flow aerodynamics have been developed and greatly facilitate the analysis and design of aeroelastic systems in the early design phase. Models capturing 95% of the physics with 8% of the modeling effort can be realized to evaluate various active and passive design considerations. A delta wing model has been developed to determine the most effective locations and shapes for transducers required to provide flutter control. The basic design philosophy is presented based upon an analytical model of the structure. A genetic algorithm was used to determine the optimal transducer locations and shapes required to provide effective flutter control based upon an open-loop performance metric. The genetic algorithm and performance metric essentially provide loop shaping through the adaptive structure design. An experimental model was developed based upon the optimal transducer designs. Wind tunnel tests were performed to demonstrate closed-loop performance for flutter control. Results from this study indicate that a single sensor/actuator pair can be designed to extend the flutter boundary and selectively couple to only those modes required to control the response.