Experimental-theoretical study of pressure distribution along the wall when a supersonic gas flow moves in an axisymmetric channel with sudden expansion

The paper describes a study of pressure distribution along the wall of an axisymmetric channel with a straight step. A supersonic gas flow formed inside the channel when an external flow with Mach numbers M = 5 and M = 6 moves around an axisymmetric model with internal duct is considered. A supersonic aerodynamic wind tunnel of a short-term action is used for experiments. The results of measuring the pressure along the channel wall in the flow around the model under study are presented. The data of aerodynamic tests are compared with the results of numerical calculations, and the resulting pressure distributions are compared. It has been established that the nonmonotonic nature of a change in pressure along the wall is caused by the shock waves, which accompany the supersonic gas flow in the channel.