A numerical study on the performance parameters of supersonic mixed compression air intake has been carried out at a design Mach number of 2.2 with and without air jets at various back-pressure ratios using a commercially available software, Ansys 2019. The k-omega turbulence model was selected to capture the viscous effects. The injection pressure and the gap between the air jets were also varied to see the effect on flow field inside the air intake. The location of the air jets was kept fixed in the longitudinal direction and the position of the normal shock was varied by changing the back pressure. Mass flow ratio, flow distortion, total pressure recovery, and skin friction coefficient were chosen to measure the performance of air intake. The results suggest that a proper combination of the number of air jets and their injection pressure can improve the performance and flow field of the supersonic air intake. Deployment of four air jets with an injection pressure ratio of 4 has shown the best performance for all back-pressure cases studied.