A Scramjet engine (Supersonic Combusting Ramjet) entails combustion at supersonic flow by generating high pressure through recompression (oblique) shock train. Shock Boundary Layer Interaction (SBLI) is an undesirable phenomenon that occurs inside the scramjet intake which has a detrimental effect on its performance. Due to adverse pressure gradient created by SBLI, the flow might be decelerated to subsonic speeds via normal shock. This leads to unstarting of the engine including other undesirable phenomena such as high drag and increased localized heating. The effect of cowl angle is studied on the performance of the scramjet engine in this study. A scramjet inlet prototype is designed in Solid Works followed by CFD analysis using ANSYS tool. The effects of cowl angle, static pressure rise, total pressure recovery and Flow Distortion are brought out. © IAEME Publication.