On the oblique breakdown mechanism in a supersonic boundary layer on a swept wing at Mach 2

A. V. Panina, A. D. Kosinov, N. V. Semionov, Yu G. Yermolaev

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

1 Citation (Scopus)

Abstract

The results of an experimental study of the controlled pulsations development in the spanwise modulated boundary layer of a swept wing are presented in the paper. The experiments were conducted at Mach 2 and unit Reynolds number Re1 = 6×106 m-1. The square stickers were applied to induce the spanwise modulation of mean flow in the boundary layer. It was obtained, that the presence of roughness leads to a decrease of the disturbance source efficiency at the subharmonic and fundamental frequency, and the oblique breakdown mechanism begins to appear at smaller values of the longitudinal coordinate × as compared with the case of a smooth wing.

Original languageEnglish
Title of host publicationProceedings of the XXV Conference on High-Energy Processes in Condensed Matter, HEPCM 2017
Subtitle of host publicationDedicated to the 60th Anniversary of the Khristianovich Institute of Theoretical and Applied Mechanics SB RAS
Editors Fomin
PublisherAmerican Institute of Physics Inc.
Number of pages5
Volume1893
ISBN (Electronic)9780735415782
DOIs
Publication statusPublished - 26 Oct 2017
Event25th Conference on High-Energy Processes in Condensed Matter, HEPCM 2017 - Novosibirsk, Russian Federation
Duration: 5 Jun 20179 Jun 2017

Publication series

NameAIP Conference Proceedings
PublisherAMER INST PHYSICS
Volume1893
ISSN (Print)0094-243X

Conference

Conference25th Conference on High-Energy Processes in Condensed Matter, HEPCM 2017
CountryRussian Federation
CityNovosibirsk
Period05.06.201709.06.2017

Keywords

  • STABILITY
  • TRANSITION
  • WAVE

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