Abstract Shock wave and boundary layer interaction (SBLI) plays important role in design of supersonic inlet for various aerospace vehicles. Flow separation induced due to shock impingement can cause increase in drag and unstart conditions both of which degrade the efficiency and performance of the intake. To address the issue of shock-induced separation, Micro Vortex Generators (MVGs) are typically placed upstream of the shock interaction point. These devices create streamwise vortices that enhance boundary layer momentum thus helping in prevention of flow separation. In this study, effect of various shapes of MVGs on SBLI was analysed using computational fluid dynamics. Specifically, MVGs with curved sidewalls were used to investigate how localized flow modification impacts SBLI control. Study has indicated that the curvature of the side wall affects the formation of streamwise vortices. MVGs with inward curved wall exhibit higher pressure gradient, resulting in formation of stronger vortex due to vortex stretching.
Chopde et al. (Wed,) studied this question.