Comparison of Direct-Numerical and Large-Eddy Simulations of Mach 11 Hypersonic Turbulent Flow over a Flat Plate
AIAA AVIATION FORUM AND ASCEND 2024（2024）
Purdue Univ
Abstract
This study presents the analysis of a Mach 11, zero-pressure gradient flow over a flat plate with an attached boundary layer and a cold-wall condition. Direct Numerical Simulation (DNS) data serves as a benchmark for evaluating the accuracy of the sub-filter scale (SFS) models used in the current study. The analysis focuses on the convergence of solutions obtained with three progressively finer grid resolutions (coarse, medium, and fine) towards the DNS data. The mean flow profiles for velocity and temperature initially exhibit good agreement with the RANS solution in the upstream section of the computational domain. This behavior reflects the dominance of the initial RANS flow field in the developing boundary layer. As the flow progresses downstream and the boundary layer evolves, the solution obtained with the SFS model exhibits progressive convergence towards the more turbulence-resolved information captured by the DNS simulation. This observation highlights the critical role of spatial dependence in the development of turbulent boundary layers. The second part of the study investigates the spatiotemporal evolution of wall parameters, such as heat flux, shear stress, and boundary layer thickness. Our observations suggest that the wall parameters predicted by the SFS models are strongly influenced by the initial RANS field in the upstream region. This influence gradually decreases as the flow progresses downstream and the solutions merge with the DNS trend.
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