Abstract
Interaction between the normal shock wave and the turbulent boundary layer in a supersonic nozzle becomes complex with an increase of a Mach number just before the shock wave. When the shock wave is strong enough to separate the boundary layer, the shock wave is bifurcated, and the 2nd and 3rd shock waves are formed downstream of the shock wave. The effect of a series of shock waves thus formed, called shock train, is considered to be similar to the effect of one normal shock wave, and the shock train is called pseudo-shock wave. There are many researches on the configuration of the shock wave. However, so far, very few researches have been done on the asymmetric characteristics of the leading shock wave in supersonic nozzles. In the present study, the effect of nozzle geometry on asymmetric shock wave in supersonic nozzles has been investigated experimentally.
Highlights
IntroductionThe supersonic flow fields with the pseudo-shock wave are observed in some apparatuses, such as the separation part of a SCRAM jet engine, a high pressure gas piping system, supersonic diffuser and so on
The supersonic flow fields with the pseudo-shock wave are observed in some apparatuses, such as the separation part of a SCRAM jet engine, a high pressure gas piping system, supersonic diffuser and so on.In the supersonic internal flow, interaction between the shock wave and the boundary layer is very complex and induces the separation of boundary layer
Interaction between the normal shock wave and the turbulent boundary layer in a supersonic nozzle becomes complex with an increase of a Mach number just before the shock wave
Summary
The supersonic flow fields with the pseudo-shock wave are observed in some apparatuses, such as the separation part of a SCRAM jet engine, a high pressure gas piping system, supersonic diffuser and so on. In the supersonic internal flow, interaction between the shock wave and the boundary layer is very complex and induces the separation of boundary layer. The series of shock waves are called shock train. This shock train and the resulting mixing region construct a pseudo-shock wave [1], which plays a role similar to that of a single normal shock wave. The leading shock wave of the pseudo-shock wave is classified into λ-type and X-type shock waves by Mach number or Reynolds number
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