Effects of local cooling on hypersonic boundary-layer stability

Furkan Oz, Kursat Kara

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

9 Scopus citations

Abstract

Sustained hypersonic flight is still a significant challenge due to increased aerodynamic heating and drag force created by turbulent boundary layers. Understanding the physical mechanisms causing the second-mode (Mack-mode or acoustic-mode) dominated laminar to turbulent transition is critical for the design of next-generation hypersonic vehicles. It has been shown that cooling a vehicle’s surface stabilizes the first-mode but destabilizes the second-mode instabilities. Our primary focus is to study the control of instability modes with the use of cooling strips locally. We conducted a direct numerical simulation (DNS) study by free stream acoustic disturbances in wave packets with wide bandwidth frequencies along with localized cooling. The flow fields were varied along the 5 half-angle blunt cone with 0.001 bluntness radius at Mach 6. By actively using a cooling system, or passively changing vehicles material characteristics, the cooling models can be achieved. The objective of this paper is to investigate the stabilization and excitation behaviors of local cooling strips with varying temperatures.

Original languageEnglish
Title of host publicationAIAA Scitech 2021 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Pages1-19
Number of pages19
ISBN (Print)9781624106095
StatePublished - 2021
Externally publishedYes
EventAIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021 - Virtual, Online
Duration: Jan 11 2021Jan 15 2021

Publication series

NameAIAA Scitech 2021 Forum

Conference

ConferenceAIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021
CityVirtual, Online
Period01/11/2101/15/21

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