Fluid-Structure Interaction in Swept Shock-Boundary Layer Interactions with Thermal Loading

The design of supersonic and hypersonic vehicles is strongly influenced by shock wave-boundary layer interactions (SBLI), which can lead to shock-induced separation, commonly known as a separation bubble, posing serious risks to vehicle performance and structural integrity. Recent studies indicate that the flow characteristics and dominant frequencies of separation bubbles differ significantly between swept SBLI and the more extensively studied unswept configurations. In this work, we investigate the combined effects of an inflow turbulent boundary layer and the aero-thermo-elastic response of a compliant panel on swept SBLI using direct numerical simulations (DNS). We examine the flow over a compliant panel located in the separation zone and explore the influence of inflow Mach number, impinging shock angle, thermal loading, and structural properties. We will discuss the key features of the flow field by identifying the dominant frequencies and correlations among key physical quantities for different swept SBLI conditions.