Characterization and Control of Vortex Breakdown over a Delta Wing at High Angles of Attack

Demands for more maneuverable and stealthy air vehicles have encouraged the development of new control concepts for separated flows. The goal of this research is the control of leading-edge vortex breakdown by open-loop, along-the-core blowing near the apex of a delta wing to improve lift and maneuverability at high angles of attack. Control is dependent on the knowledge of and the ability to detect principle characteristics of the phenomena. Therefore, an experimental study of a 700 delta wing was accomplished to better understand the physical properties of the vortical flow and the vortex breakdown phenomena. Multiple experimental methods were used to characterize the flow field and its influence on the models surfaces as well as to identify parameters for closed-loop feedback control.