Development interference type shock wave and boundary layer interference vortex flow control method

The invention relates to a control method for developing interference type shock waves and boundary layer interference vortex flow, and belongs to the technical field of aircrafts. The spoilers forming a certain angle with shock waves are arranged to interfere the development of vortexes and control vortex flow; and the height of the spoiler does not exceed the theoretical thickness of the boundary layer of the flat plate at the wedge tip so as to play a role in the boundary layer, and the spoiler has small interference on the mainstream and can reduce the influence on the flow field. By means of the control scheme, the influence area of vortexes caused by interference of shock waves and the boundary layer can be reduced, the effect of controlling the shock waves and the boundary layer to interfere vortex flow is achieved, and the method can be applied to flow control of internal flow and external flow of a high-speed aircraft. 本发明涉及一种发展干扰型激波与边界层干涉涡流动控制方法，属于飞行器技术领域。本发明通过布置与激波呈一定角度的扰流片，以干扰涡的发展，控制涡流动；且扰流片高度不超过楔