Experiments on the control of crosselow instability with the aid of suction through perforated walls

摘要

In swept wing flow of large transport aircraft,transition occurs predominantly in the leaking edge area due to leading edge contamination.Therefore,attempts to keep swept wing flow laminar have been concentrated on this wing portion.recent experiments have demonstrated that suction enables the relaminarisation of the attachment line flow [1],[2].This success inspired aircraft industry and research to study the feasibility of laminar swept wing flow by damping crossflow instability.In flight and wind-tunnel tests known so far much less success was achieved than predicted by stability analyses.