In jet engines, it is imperative to bring down the flow speeds from supersonic to subsonic level before entering the burner, in order to achieve efficient combustion. It is achieved by a series of oblique as well as normal shock waves in supersonic intakes. However, the advantage of shock enabled compression in intakes does not come standalone but with colossal losses due to shock-boundary layer interactions, which includes intake unstart and abrupt thickening/separation of boundary layer. Controlling these interactions by boundary layer control using micro-vortex generators (MVGs) has gained prominence. Here, an attempt is made to control the interactions at the shock impact point in a Mach 2.2 mixed compression intake. Two types of MVGs; a conventional and an innovative ramped-vane configuration were experimentally investigated. In both the configurations, the height of the MVGs are varied as 600μm; 400μm and 200μm. The innovative MVGs of height 200μm, showed enhanced flow mixing near the boundary layer and minimized interaction losses. These results are found in good agreement with the qualitative data. © 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.