Abstract.The technique and results of an experimental study of the flow structure and critical parameters of the flow over flat and axisymmetric bodies in a range of the Mach numbers (M = 2 ÷ 5) are presented.

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Abstract.A technique of experimental determination of the parameters and structure of supersonic air flow around of axisymmetric bodies form in the range of Mach numbers M = (2 ÷ 5) are presented. The results of the investigation of the interaction a supersonic stream flowing around of an axisymmetric model with gas jet which inject into the boundary layer are given.

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