Direct numerical simulation of crossflow instability excited by microscale roughness on HIFiRE-5

Derek J. Dinzl, Graham V. Candler

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

7 Scopus citations

Abstract

Direct numerical simulation is performed on a 38.1% scale HIFiRE-5 forebody to study stationary crossflow instability. Computations use the US3D Navier-Stokes solver to simulate Mach 6 flow at Reynolds numbers of 8.1×106/m and 11.8×106/m, which are conditions used by quiet tunnel experiments at Purdue University. Distributed roughness with point-to-point height variation on the computational grid and maximum heights of 0.5-4.0 µm is used with the intent to emulate smooth-body transition and excite the naturally-occuring most unstable disturbance wavenumber. Disturbance growth rates and wavelength evolution are analyzed, and the effect of roughness height and forcing character is considered. A steady physical mechanism for the sharp increase in wall heat flux seen in both computations and experiment is introduced. Crossflow vortex coalescence is observed and a possible cause is discussed.

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:
This work was sponsored by the Air Force Office of Scientific Research under grant FA9550-12-1-0064. The views and conclusions contained herein are those of the authors and should not be interpreted as necessarily representing the official policies or endorsements, either expressed or implied, of the funding agencies or the U.S. Government.

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

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

Fingerprint Dive into the research topics of 'Direct numerical simulation of crossflow instability excited by microscale roughness on HIFiRE-5'. Together they form a unique fingerprint.

Cite this