Stabilization of a mach 6 boundary layer using a two-dimensional cavity

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Abstract

The stability of a hypersonic boundary layer over a flat plate to wall blowing-suction with the effect of a two-dimensional cavity at different locations is investigated using direct numerical simulations. The results indicate that the second mode is damped when the cavity is placed closely downstream of the synchronization point of mode F and mode S, whereas the effect is reversed if it is located upstream and further downstream of the synchronization point. Strong damping of the disturbances is observed inside the cavity, which is found to be consistent with the thermoacoustic interpretation. It is suggested that an efficient way to stabilize the boundary layer dominated by the second-mode instabilities is to put a local cavity in the close downstream region of the synchronization point corresponding to the most dangerous frequency.

Original languageEnglish
Title of host publicationAIAA Scitech 2019 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105784
DOIs
Publication statusPublished - 6 Jan 2019
EventAIAA Scitech Forum, 2019 - San Diego, United States
Duration: 7 Jan 201911 Jan 2019

Publication series

NameAIAA Scitech 2019 Forum

Conference

ConferenceAIAA Scitech Forum, 2019
Country/TerritoryUnited States
CitySan Diego
Period7/01/1911/01/19

ASJC Scopus subject areas

  • Aerospace Engineering

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