The Separated Flows on Slender Wings in Unsteady Motion

摘要

The separated flows on slender wings in unsteady motion have been analysed using an extension of the steady state theory of Brown and Michael. Results have been computed for the cases of heaving and pitching oscillations of a slender delta wing. An unexpected phenomenon was that the vortex cores moved rapidly inboard as the wing reached zero local effective incidence. These theoretical results have been essentially confirmed by an experimental investigation in a water tunnel. The forces and damping derivatives in pitch have also been calculated and compared with experiment.