Supersonic air intakes often experience shock wave/boundary-layer interactions (SWBLIs), which result in an intricate configuration of shocks during flow deceleration. These interactions create significant fluctuations in pressure, which can pose a risk to the structural integrity of vehicle components. This chapter is an extension to the experimental findings presented by Verma regarding the use of vane-type vortex generators (VGs) to reduce separation length by simulating the flow chamber on ANSYS. The study proposes a new arrangement of VGs, combining rectangular vanes and a triangular ramp, compares the results with the reference experimental data, simulates it on a Mach 2.05 flow, and compares various configurations and control distances to determine the most effective VG model. Additionally, we have investigated the impact of different spanwise spacings between VGs on flow interaction. Computational simulations are conducted using density-based solvers and the Shear Stress Transport (SST) k-omega model. The results show that the application of VGs improves aerodynamic performance and flow stability, with the arrangement of three VGs in series outperforming the other configurations. The results are compared by various parameters and plotting their contours along with Cartesian plots.