The possibilities of manipulating shock/boundary-layer interactions are demonstrated with regard to an application for hypersonic inlets. Experiments on generic models have been carried out in the hypersonic wind tunnel of the German Aerospace Research Center at Mach 6 and laminar flow conditions. Experimental results were validated by numerical flow simulations using a two-dimensional finite element scheme. In the case of shock-induced boundary-layer separation, it could be shown that the implementation of bleed leads to a reduction of the separation bubble thickness by almost 50%. Further experimental investigations dealt with the achievable reduction of the heat loads on the wall surface depending on the amount and the position of the boundary-layer bleed. These examinations were extended to three-dimensional corner flows and favorable design parameters for a boundary-layer bleed setup were found. Finally, the results obtained using the generic models were transferred to a hypersonic inlet model. There the application of a correctly designed and positioned bleed system showed a significant increase of the attainable total pressure recovery.