Numerical Analysis of Confinement Phenomenon with Reflected Shock Waves by Opposing Wall

Abstract

We propose the shock wave confinement phenomenon as a new method for generating high-energy fields using shock waves. This study investigates the conditions for the shock wave reflection in a supersonic jets, essential for the shock wave confinement phenomenon.  The parameters of this study are the pressure ratios of the high and the low-pressure chamber of the shock tube, which are 10.7, 22.6, 35.0 and 46.0, respectively. The results show that the increased pressure ratio causes the shock wave to be reflected in the jet. The non-dimensionalized thicknesses of the low acoustic impedance near the collision between the shock wave and the jet in the acoustic impedance considering the flow velocity are 1.5, 0.9, 0.6 and 0.2 when the pressure in the shock tube varies to 10.7, 22.6, 35.0 and 46.0 respectively. The thicknesses with low acoustic impedance show similar trends in the presence or absence of shock wave reflection. Therefore, the acoustic impedance, considering the flow velocity, can qualitatively explain the reflection of the shock wave to the jet.