At cruise altitude, low Reynolds numbers result in a laminar boundary layer on the suction side of a transonic fan blade, extending to the shockwave/boundary-layer interaction. For transitional SBLIs with significant shock-induced separation, a shock oscillation mechanism occurs, characterized by the growth and natural suppression of the upstream laminar section of the separation bubble. The authors utilize a combination of numerical and experimental techniques across various cases, including a canonical case, cascades, and a 3D fan, to investigate the phenomenon. To validate the dynamic mechanism observed in large eddy simulations, experiments using high-speed Schlieren, spark light sh dowgraphy and PIV were conducted. The characteristic length scale for the oscillation mechanism, based on the travel distance of the laminar separation shock, is a key finding. The mechanism existence strongly depends on free stream turbulence and the boundary layer state. Oscillation frequencies are much lower for the turbulent oncoming boundary layer compared to the laminar case, which shows a strong link between the large scale movement of the laminar separation shock, the separation bubble, and reflected shock movement. In contrast, the turbulent interaction shows significantly less reflected shock travel distance. Preliminary full span LES simulations corroborate the link of findings to the application.