Development and validation of a LES turbulence wall model for compressible flows with heat transfer

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

4 Scopus citations

Abstract

The numerical simulation of turbulent hypersonic flows poses a number of significant challenges. Chief among these challenges is the stringent grid resolution requirement in the boundary layer to accurately predict wall heat ux and skin friction. An enabling modeling concept for such flows is the use of wall models to reduce the near wall compu-tational burden. In this paper, we present the development and validation of a turbulence wall model applicable to high Reynolds number flows. We review modeling choices that arise given a use case of cold-wall hypersonic flow with shock-turbulent boundary layer interaction. Finally, we assess the performance of the model in an a posteriori analysis of a hollow cylinder-are forebody and a large cone-are forebody, and comment on model performance and limitations.

Original languageEnglish (US)
Title of host publication54th AIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624103933
DOIs
StatePublished - 2016
Event54th AIAA Aerospace Sciences Meeting, 2016 - San Diego, United States
Duration: Jan 4 2016Jan 8 2016

Publication series

Name54th AIAA Aerospace Sciences Meeting
Volume0

Other

Other54th AIAA Aerospace Sciences Meeting, 2016
CountryUnited States
CitySan Diego
Period1/4/161/8/16

Bibliographical note

Funding Information:
The authors would like to acknowledge the efforts of all of the institutions supporting the Air Force Research Laboratory?s Collaborative Center for Aeronautical Sciences, as well as the Boeing Corporation for their support of this work.

Publisher Copyright:
© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA . All rights reserved.

Copyright:
Copyright 2020 Elsevier B.V., All rights reserved.

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