Experimental research of spatial inlet based on an corner configuration with a Mach interaction of shock waves

The paper is focused on the research of the spatial way of flow inhibiting applied to supersonic and hypersonic input devices of aircrafts. To inhibit the flow a structural element, the corner body, is used. It provides spatial compression from the leading edge of the input device while the second (reflected) shock wave is formed in the non-contiguous flow area. The results of an experimental research of two spatial inlets based on the flow in a corner body with the Mach interaction of shock waves are presented.