Choosing DES, LES, or URANS for Aeroacoustics
Where boundary layer structures do not directly affect the aeroacoustics, DES and LES using Bounded Central Differencing perform similarly in terms of pressure spectra.
LES is quicker as it solves fewer equations. When the hybrid BCD discretization scheme is used in DES, some key regions, such as an A-pillar or separated shear layers, suffer from numerical damping of the pressure fluctuations. The guideline (at this time) is to resolve the boundary-layer down to y+ equal to 1.
In general, Unsteady Reynolds Averaged Navier Stokes (URANS) is not recommended, unless the flow features are guaranteed to be tonal (such as obtained from blade passing or coherent shedding). Never use URANS when there is broadband content arising from turbulence. DES uses RANS only in the boundary layer. RANS-type meshes are sufficient in the bulk flow (away from boundary layers). You can investigate the mesh suitability by interrogating the spatial distribution of the turbulence integral scales arising from a steady RANS calculation. Use a mesh size less than 0.5x(local integral turbulence length scale).