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.

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