A technique of flux reconstruction at the interfaces of nonconforming grids for aeroacoustic simulations. (23rd October 2019)

• Record Type: Journal Article
• Authors: Le Bras, Sophie; Deniau, Hugues; Bogey, Christophe
• Is Part Of: International journal for numerical methods in fluids. Volume 91:Number 12(2019)
• Page Start: 587
• Page End: 614
• Publication Date: 2019-10-23
• Subjects: aeroacoustics -- finite volumes -- high‐order schemes -- meshless interpolation -- nonconforming grids -- structured grids; Fluid dynamics -- Mathematics -- Periodicals; 532
• DOI: 10.1002/fld.4767
• Languages: English
• ISSNs: 0271-2091

Abstract

Summary: A flux reconstruction technique is presented to perform aeroacoustic computations using implicit high‐order spatial schemes on multiblock structured grids with nonconforming interfaces. The use of such grids, with mesh spacing discontinuities across the block interfaces, eases local mesh refinements, simplifies the mesh generation process, and thus facilitates the computation of turbulent flows. In this work, the spatial discretization consists of sixth‐order finite‐volume implicit schemes with low‐dispersion and low‐dissipation properties. The flux reconstruction is based on the combination of noncentered schemes with local interpolations to define ghost cells and compute flux values at the grid interfaces. The flow variables in the ghost cells are calculated from the flow field in the grid cells using a meshless interpolation with radial basis functions. In this study, the flux reconstruction is applied to both plane and curved nonconforming interfaces. The performance of the method is first evaluated by performing two‐dimensional simulations of the propagation of an acoustic pulse and of the convection of a vortex on Cartesian and wavy grids. No significant spurious noise is produced at the grid interfaces. The applicability of the flux reconstruction to a three‐dimensional computation is then demonstrated by simulating a jet at a Mach number of 0.9 and a diameter‐based Reynolds number of 4×10 5 on a Cartesian grid. The nonconforming grid interface located downstream of the jet potential core does not appreciably affect the flow development and the jet sound field, while reducing the number of mesh points by a factor of approximately two. Abstract : A flux reconstruction technique is presented to perform aeroacoustic computations using implicit high‐order spatial schemes on multiblock structured grids with non‐conforming interfaces. The use of such grids with mesh spacing discontinuities across the block interfaces eases local mesh refinements, simplifies the mesh design, and thus facilitates the computation of turbulent flows. The performance of the flux reconstruction is demonstrated by simulating the propagation of an acoustic pulse, the convection of a vortex, and the development of a round jet flow.