Wall modeled LES of compressible flows at non-equilibrium conditions

Balachandra R. Mettu, Pramod K. Subbareddy

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

3 Scopus citations

Abstract

Wall modeled large eddy simulation (WMLES) was performed using the equilibrium wall model on cases which involved hypersonic Mach numbers and cold wall conditions. A modified transition sensor was formulated which seems to show much better behavior in the laminar region compared to the original sensor when tested in a transitional shock boundary layer interaction case. The sensor is dynamically able to predict the laminar to turbulent transition without any input from the wall model. The heat flux predictions showed reasonable accuracy in the transitional region for the coarse resolution used in this case. In the cold wall boundary layer case a delay in transition was observed and a slight overprediction in the wall shear stress and heat flux in the turbulent regime. There seemed to be good agreement with the mean velocity and temperature profiles. The temperature peak in the inner layer was accurately captured by the wall model. The wall model showed deficiencies when tested in a flow over a compression ramp owing to the strong non-equilibrium conditions in the shock-boundary layer interaction region. The separation length was under-predicted with significant under-prediction in the peak wall pressure and heat flux.

Original languageEnglish (US)
Title of host publication2018 Fluid Dynamics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105531
DOIs
StatePublished - 2018
Externally publishedYes
Event48th AIAA Fluid Dynamics Conference, 2018 - Atlanta, United States
Duration: Jun 25 2018Jun 29 2018

Publication series

Name2018 Fluid Dynamics Conference

Other

Other48th AIAA Fluid Dynamics Conference, 2018
CountryUnited States
CityAtlanta
Period6/25/186/29/18

Bibliographical note

Funding Information:
We gratefully acknowledge support from the AFOSR High-Speed Aerodynamics Program, with Dr. Ivett Leyva as Program Manager. 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.

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