shock train

inlet

blunt body

normal shock

total pressure

plasma actuator

dynamic mode

flow control

mach number

fluid-structure interaction

Acta Astronautica

The shock wave/boundary-layer interaction is a common phenomenon, and it occurs in the internal and external flow fields of the hypersonic vehicle. Then, the separation, the oscillatory flow structures, the heat transfer localization and the pressure loads would be induced accordingly. In this survey, recent advances on the shock wave/boundary-layer interaction and its control in the internal and external flow fields were summarized, and it is obvious that the micro-vortex generator has been widely used in both the internal and external flow fields to suppress the separation induced by the shock wave/boundary-layer interaction, and the quantitative measurement and assessment approaches should be developed. At the same time, the intelligent control approach should be combined with the flexible surface to fit the variation of the incoming boundary conditions. With the development of the hypersonic flight technique, the requirement of the wind tunnel with high Mach number is urgent, as well as its test time. At the same time, the Monte Carlo method is required to obtain the shock wave/boundary-layer interaction properties in the high Mach number. • Shock wave/boundary layer interaction and its control in internal and external flow fields was reviewed. • Intelligent control approach was proposed to control the interaction with the flexible surface. • Quantitative measurements and assessment approaches should be developed to evaluate the separation size. • Interaction and its control in the high Mach number and high altitude should be evaluated.

Recent advances in the shock wave/boundary layer interaction and its control in internal and external flows