Aero-Thermo-Elastic Analysis of Swept Shock Wave-Boundary Layer Interaction

Flow characterization of the shock wave boundary layer interaction (SBLI) is crucial in various supersonic and hypersonic aerospace applications. In this study, we investigate and characterize the effect of the inflow turbulent boundary layer and aero-thermo-elasticity of a compliant panel on the swept SBLI through direct numerical simulations (DNS). A compact finite difference solver is coupled with a finite element structural solver through a partitioned fluid-structure interaction (FSI) framework. A sharp-interface immersed boundary method is employed for the fluid-thermal-structure coupling. The main objective of this study is to investigate the effect of the compliant panel in the interaction zone of the swept SBLI. The results show that the sweep inflow alters the flow features by increasing the interaction zone, flow reversal region, intensity of low-frequency content of surface pressure fluctuations, and amplitude of panel oscillations. Cooling results in low amplitude and high-frequency panel oscillations. The dominating frequencies of panel oscillations are observed as high-frequency footprints in surface pressure fluctuations in the case of sweep inflow.