With the growing interest in the research community of hypersonic vehicles, there has been tremendous research conducted worldwide on the hypersonic shock-wave boundary layer interaction. This phenomenon is profound, especially in the vicinity of the intake of a scramjet engine, whose forebody is composed of multiple wedges to facilitate the external compression of the intake air. However, due to the viscous nature of the fluid, the boundary layer interacts with the shock waves originating from multiple compression corners, which offers adversities in the form of flow separation. The various shock-shock interaction complicates the flow field further. Prominent studies were conducted with the help of canonical geometries such as a double-wedge configuration in past to understand these phenomena experimentally as well as numerically. However, most of the studies relied on the geometry having a sharp leading edge. In order to reduce the separation size of the bubble and peak loads of pressure and heat transfer rate at the leading edge, some amount of bluntness can be added to reduce them. However supplementing this geometry with bluntness, the flow field is drastically altered as compared to the flow field associated with the sharp leading edge. In this video, we try to explain the effect of adding bluntness of various degrees (R/L1=0.025 & 0.25) to the sharp double-wedge configuration and try to give a glimpse of the flow features associated with them.