Multiple-Actuator Control of Vortex Breakdown on a Pitching Delta Wing

摘要

Although the phenomenon of vortex breakdown on delta wings has been known since the early 1960s, only recently have investigations concentrated on control of the breakdown location on maneuvering delta wings. Quantitative interpretations of the flow patterns via particle image velocimetry during pitching motion are given by Magness et al.1 and Cipolla and Rockwell.2 Overviews of the control of vortex breakdown on pitching delta wings from numerical and experimental views are provided by Visbal3 and Rockwell,4 respectively. The consequences of unsteady blowing-suction at the leading edge and blowing at the trailing edge, applied to a stationary wing, are described respectively in the investigations of Gu et al.5 and Helin and Watry.6 Not yet investigated is simultaneous control applied at the leading and trailing edges during pitching motion of the delta wing.