This paper validates an existing scramjet intake design and provides suggestions on improving its performance by using micro ramps. The intake of this particular scramjet has an unsteady phenomenon ‘shock wave boundary layer interaction’ (SBLI). When an impinging shock comes in contact with a developing boundary layer, it causes the boundary layer to thicken and separate. This leads to an inferior performance of the engine. Micro Ramps or Micro Vortex Generators (MVG) were used to counteract these effects, by producing a pair of counter-rotating vortices. This suppresses the SBLI and precludes flow separation. The effect of micro ramps on alleviating SBLI was studied on the performance of the scramjet engine in this work. Single micro ramp was placed along the centreline of the ramp surface at distances 1/3rd, ½ and 2/3rd from the leading edge and the separation bubble. Flow simulations were done. The results showed that single micro ramp placed at mid distance between the leading edge and separation bubble gave better performance. It eliminated the separation bubble to a maximum extent. The improvements in the static pressure and stagnation pressure were also noticed. As the micro ramp moved closer to the place of impingement of oblique shock from the cowl edge on the boundary layer, it is found that the separation bubble size increases. An array of micro ramps were also placed at mid-way along the ramps surface and simulations were done. The results obtained revealed that the flow performance has been enhanced by reduction in the separation bubble size. © 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.