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Interaction between turbulent boundary layer and slowly moving oblique shock train was investigated in a long constant-area duct, simulating Mach 2.5 isolator flow experimentally. Two different types of schlieren techniques were employed to visualize the unsteady interaction while measuring the corresponding wall pressure on the top and bottom. For visualizing the entire length of the isolator, a background oriented schlieren (BOS) technique was customized and implemented in the present study. The flow-field images were then compared with those obtained from a conventional schlieren technique. The correlated results elucidated the relationship between shock train movement and evolving pressure gradient, which caused boundary layer separation immediately downstream of the shock train. The paper contains not only the time-resolved schlieren images corresponding to various pressure data but it also describes the optimization of the background pattern and the implementation of the BOS for the current experiment.