This study investigated the control of Shock-Wave/Boundary-Layer Interactions (SWBLI) using jet actuators at several locations, both upstream and within the separation bubble. Such interactions are critical in high-speed aerodynamic applications, where flow separation can lead to performance losses. Using Large Eddy Simulation (LES), the effects of injection on the separation region are studied. Where both the time-averaged as unsteady effects are examined. The results show that size reduction of the separation bubble is not effective when the actuators are placed within the separation region. However the actuators were able to modulate the large scale motion of the separation independent of the injection frequency or location. Indicating that the instabilities of SWBLI are potentially inherent and can be modulated from within the bubble. The proposed driving mechanism behind this are the pressure disturbances created by the injection, which is supported by the results.