This study conducts a thorough analysis of shock-wave/boundary-layer interaction (SWBLI) phenomena and their subsequent effects on aerodynamic performance. Significant attention is given to the effectiveness of vortex generators in improving the adverse effects of shock wave boundary layer interaction (SWBLI) and preventing the occurrence of flow separation issues. The study presents the results of research examining the use of dynamic injection-based vortex generators with adjustable pressure values. It emphasizes their impressive potential to improve flow efficiency, stability, and overall performance in various operational situations. In addition, the research presents a detailed computer study that carefully examines the different effects of injecting various sizes of fluid into a microvortex generator (MVG) placed in a supersonic air intake duct. The analysis utilizes contour plots and graphical data representations to provide a thorough comparison of the resulting flow dynamics. This thorough analysis contributes to a detailed comprehension of the impact of variations in injection size on the mitigation of shock-wave/boundary-layer interactions (SWBLI) and its consequences for improving aerodynamic performance.