Modelling of Turbulent Flows at LAST, Tsinghua University

Abstract

The Laboratory for Advanced Simulation of Turbulence (LAST) at Tsinghua University had been working on turbulence modeling for almost two decades. Previous work includes the nonlinear eddy-viscosity model satisfying the realizability condition, the BGK gas kinetic scheme, the numerical simulation of supersonic mixing layers, etc. Recently, the modeling work had been concentrated on compressible turbulent flows and supersonic/hypersonic boundary layer flow transition. This presentation is thus focused on the latter two topics.

Compressibility is well known to suppress turbulence, the cause of the compressibility effects remains, however, unclear. Previous studies carried out in the early 1990s conjectured that the main compressible effects were associated with the dilatations of velocity fluctuation. Later, it was shown that the main compressibility effect came from the reduced pressure-strain term due to reduced pressure fluctuations. Although better understanding of the compressible turbulence had generally been achieved with the increased DNS and experimental efforts, there are still some discrepancies among these recent findings. In the present work the effect of compressibility on shear flows are characterized in three categories corresponding to three regions of turbulent Mach numbers M_t: the low-M_t, the transition-M_t and the high-M_t regions. It is observed in these three regions that the effect of compressibility on the growth rate of the turbulent mixing layer is rather different. A simplified approach to model the reduced pressure-strain effect may not necessarily reduce the mixing-layer growth rate, rather, an increase in the growth rate may occur. The present work develops a new second-moment model for the compressible turbulence through the introduction of some blending functions of M_t to account for the compressibility effects on the flow. The model has successfully applied to the compressible mixing layers.

In the supersonic/hypersonic boundary layer flow transitions, it is known that the most unstable mode, over certain range of Mach number, differs from the traditional incompressible case. The second or even higher unstable modes can occur and dominate the instability of the flow, hence, influencing the flow transition to turbulence. The present work takes the second instability mode into modeling consideration, a new transition model is proposed which shows reasonably good performance in high speed, as well as in slow speed, flow transitions.