Active flow separation control using synthetic jet actuators

Due to the character of the original source materials and the nature of batch digitization, quality control issues may be present in this document. Please report any quality issues you encounter to digital@library.tamu.edu, referencing the URI of the item.Includes bibliographical references (leaves 59-60).Issued also on microfiche from Lange Micrographics.The use of synthetic jet actuators for controlling the boundary layer flow and flow separation over a wing is investigated. A theory for the optimum design of actuators using motors is developed. A motor driven synthetic jet actuator is built and validated for separation control in the water tunnel. Flow visualization and quantification is accomplished using particle image velocimetry. These experiments also focus on the enhancement of mixing of flow and the propagation of dominant structures in the separated region of the wing, induced by the actuators. Characterization of the modification in the pressure distribution and loading on the wing is undertaken to apply SJAs for aeroelastic control of a wing. A piezoelectrically driven SJA is built and embedded inside a 0.2 m chord wing with a NACA 0015 cross section. This wing is tested for alteration in the pressure coefficient (C[]) profile of the cross section with the actuation of the SJA