Research Progress of Microjet Control of Shock Wave/Boundary Layer Interactions in Supersonic Flow Field

Abstract

The phenomenon of shock wave/boundary layer interaction is inevitable in the supersonic flow field. The existence of this phenomenon will have a series of adverse effects on the inner and outer flow fields of the supersonic vehicle. Therefore, it is necessary to control the shock wave/boundary layer interaction. Microjet active flow control method has become a research hotspot in the field of flow control in recent years. This paper summarizes the latest research progress of microjet active flow control method in the control of shock/boundary layer interaction, comprehensively analyzes the factors affecting the control effect of single-hole microjet and microjet arrays. In addition, it discusses the shortcomings and development prospects of current research. This paper can provide some references for related research.

Keywords

• |shock wave/boundary layer interactions|flow separation|microjet|flow control|vortex pair|flow field|supersonic vehicle