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Dns/les of supersonic turbulent boundary layer using compact interpolation method
, Modi B.
Published in
Pages: 1 - 13
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. © 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
About the journal
JournalAIAA Scitech 2021 Forum
Open AccessNo