Dual Numerical Solution for 3D Supersonic Laminar Flow Past a Blunt-Fin Junction: Change in Temperature Ratio as a Method of Flow Control

Abstract

The results of a numerical solution of the problem of supersonic flow past a blunt fin mounted on a plate with a developing boundary layer are presented. The initial formulation of the problem is based on the presented in the literature computational and experimental investigation, in which the laminar flow regime was studied for the fin perpendicular to the plate at the free-stream Mach number equal to 6.7. Earlier, the authors showed (2020) that under these conditions there exist two stable solutions to the problem. These solutions correspond to the metastable states of flow with different configurations of the vortex structure and different patterns of local heat transfer. In the present study, the influence of a temperature ratio on the vortex structure in the separation region, local heat transfer, and the possibility of obtaining a dual solution are investigated. The ability to switch between solutions of two types using a short-time change in the plate temperature ratio are shown.

Response of the Shock Wave/Boundary Layer Interaction to Disturbances Induced by the Plasma Discharge

“…ary layers [26,27]. This increased attention is driven by the potential flows in the design of partially laminar aircraft and on the blades compressors intended for high-altitude operation.…”

“…However, it is important to note that, at sufficiently low Reynolds numbers, the boundary layer can be laminar. In recent years, there has been a growing interest in the interaction of shock waves with laminar boundary layers [26,27]. This increased attention is driven by the potential applications of such flows in the design of partially laminar aircraft and on the blades of turbofan engine compressors intended for high-altitude operation.…”