Modeling non-equilibrium effects in wall modeled les of high-speed flows

Balachandra R. Mettu, Pramod K. Subbareddy

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

We explore the use of wall modeled large eddy simulation (WMLES) in the context of compressible flows with shock-induced separation. A novel feature of the non-equilibrium model used is that it doesn’t require the explicit generation of an auxiliary mesh. The nonequilibrium model has shown good results in all the regions where the boundary layer is attached and performed much better compared to the equilibrium model in separated regions. The bottleneck for these cases seems to be the use of an eddy viscosity model which is derived based on the assumption that the boundary layer is attached. The classic damping functions computed using the local friction velocity cause unphysical damping of eddy viscosity in separated regions. A modified algebraic model using a velocity scale based on the pressure gradient was tested on the shock-boundary layer interaction (SBLI) cases. This eddy viscosity was modeled such that it reverts to the classic mixing-length model in attached regions and does not excessively damp the eddy viscosity in separated regions. The modified eddy viscosity did lead to better skin-friction results in the separated region but it also led to a slight expansion of the separation bubble due to excessive eddy viscosity in the upstream region of the shock-interaction.

Original languageEnglish (US)
Title of host publicationAIAA Aviation 2019 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Pages1-17
Number of pages17
ISBN (Print)9781624105890
DOIs
StatePublished - 2019
Externally publishedYes
EventAIAA Aviation 2019 Forum - Dallas, United States
Duration: Jun 17 2019Jun 21 2019

Publication series

NameAIAA Aviation 2019 Forum

Conference

ConferenceAIAA Aviation 2019 Forum
Country/TerritoryUnited States
CityDallas
Period6/17/196/21/19

Bibliographical note

Funding Information:
We gratefully acknowledge support from the AFOSR High-Speed Aerodynamics Program. This material is based upon work supported by the Air Force Office of Scientific Research under award number FA9550-17-1-0157. Any opinions, finding, and conclusions or recommendations expressed in this material are those of the author(s) and do not necessarily reflect the views of the United States Air Force.

Publisher Copyright:
© 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

Fingerprint

Dive into the research topics of 'Modeling non-equilibrium effects in wall modeled les of high-speed flows'. Together they form a unique fingerprint.

Cite this