Block Interface Flux Reconstruction Method with Nonlinear Scheme for Aeroacoustics Problem

What is it about?

Non-conforming grids, which can reduce the complexity of generating meshes for complex shapes and minimize the number of meshes, are commonly utilized to address linear or nonlinear aeroacoustics problems by simulating sound propagation processes at a reasonable cost. In this context, a flux reconstruction technique is proposed to effectively implement nonlinear schemes on non-conforming grids. The technique is specifically designed for 6th-order finite difference compact nonlinear schemes and is based on the combination of non-centered schemes with local interpolations to reconstruct ghost cells and flux values at grid interfaces. To enhance the stability of the nonlinear scheme at the grid interface, we have adopted an optimized Lagrange interpolation method proposed by Tam et al., which significantly expands the application range in wavenumber domain. Additionally, different time step scale algorithms for time advancement are employed to improve calculation efficiency.

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