This study discusses the performance enhancement of supersonic air intake model through different control techniques and hybrid control such as local cooling, concavity and convexity inside the isolator. A Mach number 5 model developed by the Azam Idris1 studied and validated by numerical simulation to regenerate the results for further developments and comparisons. Ansys Fluent version 18 is used to numerically simulate the model. A Comparison of numerical simulation and experimental measurements is presented to validate the correctness and accuracy of the numerical framework followed in the current study. Refined mesh with boundary control accuracy is used for the simulation purposes as it will generate precise results. Different techniques are used to control the flow and enhance the performance at the outlet. In certain cases, it is noticeable that flow separation is reduced to a great extent and increase in the total pressure is appreciable. Hybrid control can reduce the strength of shock wave boundary layer interaction and the separation bubble occurring at shoulder junction, cowl lip and inside the upper part of isolator. Increase in total pressure recovery and decrease in flow distortion clearly show that the hybrid control techniques can effectively be supersonic air intake systems. © 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.