Numerical study of the interaction of the supersonic flat-plate boundary layer with an oblique incident shock

Abstract

A numerical study of the effects of disturbances on the interaction of a transitional supersonic flat-plate boundary layer with an incident oblique shock has been carried out. Direct numerical simulation of the transitional boundary layer on a flat plate is performed by solving the Navier–Stokes equations using two different CFD codes: parallel code CFS3D and hybrid parallel code HyCFS. The simulation is carried out in a three-dimensional computational domain at free-stream Mach number M = 1.45, which corresponds to the conditions of the experiments. At first stage, the transitional boundary layer is computed without an incident shock wave. Development of the disturbances introduced at the inflow boundary causes formation of a secondary flow in the form of three-dimensional longitudinal vortex structures that leads to the laminar-turbulent transition farther downstream. At the second stage, boundary conditions corresponding to the parameters behind an oblique shock are specified on a part of the upper boundary of the computational domain. As a result of the interaction of the boundary layer with an incident shock in the reflection region, a separation zone is formed. The presence of large-scale eddies developing in the boundary layer causes significant oscillations of the separation zone. Due to the shock wave boundary layer interaction the laminar-turbulent transition shifts upstream towards the separation region.A numerical study of the effects of disturbances on the interaction of a transitional supersonic flat-plate boundary layer with an incident oblique shock has been carried out. Direct numerical simulation of the transitional boundary layer on a flat plate is performed by solving the Navier–Stokes equations using two different CFD codes: parallel code CFS3D and hybrid parallel code HyCFS. The simulation is carried out in a three-dimensional computational domain at free-stream Mach number M = 1.45, which corresponds to the conditions of the experiments. At first stage, the transitional boundary layer is computed without an incident shock wave. Development of the disturbances introduced at the inflow boundary causes formation of a secondary flow in the form of three-dimensional longitudinal vortex structures that leads to the laminar-turbulent transition farther downstream. At the second stage, boundary conditions corresponding to the parameters behind an oblique shock are specified on a part of the upper bou...