| Shock wave boundary layer interactions (SWBLIs) occur when a shock wave meets a boundary layer. This study aims to isolate the interaction through numerical investigation of a normal SWBLI and build knowledge of the computational fluid dynamics software, Wind-US 3.0. The test geometry, based on the experimental work of Bruce et al [16], contains a two-dimensional duct split into upper and lower channels by a shock holding plate. The boundary conditions were based on experimental conditions, and include: an inlet Mach number of 1.6; inlet total pressure and temperature of 62.5 psi and 522 degrees R, respectively; and viscous walls on all physical surfaces. Downstream boundary conditions are varied in attempts to produce a correct shock structure throughout the domain. This study uses two-dimensional structured grids containing approximately 832,000 elements. Wind-US solves the Reynolds-Averaged Navier-Stokes equations using Roe's second-order upwind-biased flux-difference splitting algorithm with a total variation diminishing (TVD) limiting parameter. The turbulence model selected for this study was the Menter SST k-o model. Attempts to produce the correct shock structure have included varying the downstream boundary conditions, changing the number of cycles and associated Courant-Friedrichs-Lewy, TVD, and grid sequencing parameters. This study used several tutorial files available through the NPARC Alliance to establish the analysis settings needed to produce a shock wave in the lower channel. This enables progress to be made on the next step of this project which is to simulate and analyze the interaction of a normal SWBLI in two dimensions. Results illustrate the correct combination of boundary conditions necessary to generate a shock in the expected location. In addition, an appropriate zonal configuration has been determined to eliminate the horizontal zone interfaces which can cause non-physical behavior in those locations. |
