A Study on Pseudo-Shock Wave Formation Mechanism

Abstract

The characterization of pseudo-shock wave which is made by interaction between a shock wave and boundary layer is important for various aerospace engineering purposes including the isolator in a scram jet engine. In the present paper, two-dimensional numerical simulation was conducted to reveal physically how the shock-boundary layer interaction produces a pseudo-oblique shock wave for a supersonic channel flow with a slender obstacle located at the center downstream. It is found that a high-speed jet against the supersonic main flow which is issued from the attachment point of a shock wave with the channel wall is the main mechanism for the formation of a series of reverse flow regions in the pseudo-shock wave.