Shock wave boundary layer interaction in a hypersonic laminar flow on a hollow cylinder flare

Mahsa Mortazavi, Doyle Knight

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

3 Scopus citations

Abstract

Shock wave boundary layer interaction over an axisymmetric hollow cylinder flare creates a complex flow structure due to the adverse pressure gradient imposed on the boundary layer and the formation of the multilayer shock wave structure. This phenomenon can be critical due to its unsteady nature and the low frequency load it applies on the vehicle at hypersonic speeds. Understanding this phenomena and finding techniques to control it is very important for flights at high Mach numbers. The prediction of the heat transfer on the vehicle in hypersonic speeds with shock wave boundary layer interaction can be very complicated. The capability of numerical models to predict the pressure and heat transfer on the vehicle with shock wave boundary layer interaction is up to debate. This research deals with the assessment of the laminar perfect gas model to predict the pressure and heat transfer on a hollow cylinder flare in a flow at Mach 10. The numerical results are compared with experimental data for validation.

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
Country/TerritoryUnited States
CitySan Diego
Period1/4/161/8/16

ASJC Scopus subject areas

  • Aerospace Engineering

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