Multiple shock wave turbulent boundary layer interactions and its oscillations are present in constant or nearly constant area ducts such as scramjet inlets, supersonic ejectors, supersonic wind tunnels etc. Under certain conditions, a series of normal shock pattern called shock train may form and can cause highly non-uniform and unsteady flow downstream of the interaction. The parameters which affect the structure of this shock pattern is well studied for steady state analysis, but the possible reasons for the oscillation characteristics is not yet understood very well. Some extensive works carried out in this regards fails to understand the mechanism of oscillations in these internal flow situations. The present study focuses on these mechanisms and the effect of each parameter changes on the multiple shock wave oscillations. The transient effects of shock oscillations are investigated using a finite volume solver initially and then experimentally. The variation in the mean shock position is analyzed through the wall static pressure distribution and shock location images