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DNS/LES of Supersonic Turbulent Boundary Layer using Compact Interpolation Method

AIAA 2021-1670
Session: Turbulent Flows III
Published Online:https://doi.org/10.2514/6.2021-1670
Abstract:

View Video Presentation: https://doi.org/10.2514/6.2021-1670.vid

A finite volume based numerical method for simulating supersonic turbulent boundary layer over a flat plate is suggested. A sixth-order compact interpolation method is used for computing fluxes at the cell interfaces. A rescaling method for generating inflow turbulence is discussed to provide realistic inflow conditions at the inlet. DNS and LES are conducted for Mach 2 zero pressure gradient turbulent boundary layer. Mean velocity profiles and turbulent intensities are validated.