Flow separation from yawed delta wings

Abstract

The flow over a flat plate delta wing at incidence and yaw is studied using a vortex-sheet model. The numerical method adopted allows solutions to be obtained in regions of parameter space, in particular at low incidence, where previous methods have failed to converge. In the results which are presented attention is focussed upon these new solutions. Where comparable the agreement with the available experimental results is encouraging. For large angles of yaw the leeward leading edge becomes a trailing edge and the associated vortex sheet assumes the characteristics of a trailing edge sheet. A simple analytical model for such a trailing vortex system is also studied. The results predicted by this linear model compare favourably with those from a further numerical study which indicates that the non-linear behaviour is similar to that of a flat wake and confirms the asymptotic nature of the linear model.