The interaction between shock waves and thick boundary layers formed on the surface of an aircraft results in complex phenomena of shock wave/boundary layer interaction (SBLI). Local damage and rapid material fatigue on the aircraft’s surface, severely affecting aircraft safety, can be attributed to the peak heat flux within the turbulent boundary layer interaction zone and the low-frequency oscillation characteristics of shock waves. In this study, the unsteady characteristics of shock wave-turbulent boundary layer interactions were investigated in hypersonic wind tunnel at the China Academy of Aerospace Aerodynamics. Advanced testing methodologies, such as infrared thermographic technology, fluctuation pressure measurement technology, and high-speed laser schlieren technology, were utilized to acquire data on flow topology, wave system structure, surface heat flux, and oscillation frequency of separation shock within the interaction zones of 34° and 42° flat plate compression corner models at a Mach number of 4.97. A significant increase in heat flux within the separation zone was observed. Furthermore, a bimodal distribution of the power spectral density within the turbulent boundary layer was identified, with frequencies of approximately 6 kHz and 30 kHz, respectively. Low-frequency predominance, around 0.2 kHz, was noted within the intermittent zone, transitioning to high frequency, approximately 30 kHz, within the separation zone.