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Flow control to prevent or delay boundary layer separation can dramatically improve the performance of air vehicles in critical regions of the flight envelope. Prior aerodynamic experim ents have shown that unsteady excitation, at the appropriate frequency, can delay boundary layer separation more effectively than steady flow perturbations. An electro - mechanical flow control device, with a substantial deployment frequency bandwidth, has been developed and tested in both static and dynamic flow control environments. The device couples a high frequency piezostack actuator with a sixty five -to -one displacement amplification mechanism to oscillate sixteen vortex generating blades at rates up t o two hundred hertz. Conceptual design of the piezostack -compliant mechanism is discussed. Flow separation control results are presented and device performance issues including dynamic characteristics are addressed.

An Adaptive Structures Electro-mechanical Device for Dynamic Flow Control Applications