Computational Study of Laminar and Turbulent Shock Wave Boundary Layer Interactions at Mach 5

Shock wave boundary layer interaction (SWBLI) is a key phenomenon in high-speed aerodynamics, influencing aerodynamic efficiency, stability, and thermal loading. This study employs the SU2 solver to investigate SWBLI in laminar and turbulent regimes. Initially, two-dimensional turbulent cases for a flat plate and three different wedge angles (6°, 10°, and 14°) are validated against experimental data to ensure numerical accuracy. The analysis then focuses on laminar interactions, where low-momentum boundary layers are more susceptible to shock-induced adverse pressure gradients, leading to flow separation, recirculation bubbles, and delayed recovery. Reynolds number effects are examined by systematically reducing freestream pressure and temperature, thereby altering both shock strength and viscous properties. Results indicate that lower Reynolds numbers generate weaker shocks and shorter separation bubbles with earlier reattachment, whereas higher Reynolds numbers produce stronger shocks, longer bubbles, and delayed reattachment despite higher boundary layer resistance. In addition, transitional flow cases also investigated to observe the onset and development of transition within the interaction region, providing further insight into the intermediate regime between laminar and turbulent SWBLI. The study highlights the coupled influence of Reynolds number, freestream conditions, and boundary-layer state on SWBLI, enhancing predictive capability for high-speed vehicle design and optimization.