Interaction of Boundary Layer with Shock Wave in Unsymmetrical Supersonic Nozzle

Abstract

The study of unsymmetrical nozzle flow is important not only for basic research in gas dynamics but also for mechanical applications. In the present study, six kinds of unsymmetrical nozzles which had different divergence angles and wall lengths were used to analyze the effect of the nozzle configuration and Mach number at the nozzle entrance on the flow. The effects of Mach number at the nozzle entrance and the divergence angle of the nozzle on the oscillation of shock wave were investigated experimentally. Furthermore, the effect of wall length on the direction of the flow was investigated. A schlieren optical system, and a Mach-Zehnder interferometer composed of an Argon laser (CW) as the light source with acousto optic modulators (AOM) were employed for visualization of the flow.