This program addresses the unsteady flow structure and loading of delta wings subjected to controlled pitching motion. Efforts are focussed on three primary areas: generation of computer-aided techniques for quantitative interpretation of flow structure; development of new types of experimental instrumental and facilities; and characterization of the unsteady flow structure on delta wings. Computer applications for quantitative visualization of the vortex structure involve tracking of hydrogen bubble timelines and particles illuminated by scanning lasers. These techniques are integrated with active control systems that generate prescribed pitching motion of delta wings. Characterization of the unsteady flow structure is concerned with the response of the vortex breakdown to the motion of the wing and with preliminary consideration of the instantaneous cross-sectional structure of the leading edge vortices. The phase lag of these features of the flow structure, relative to the wing motion, is a central consideration.