On introduction of controlled disturbances into a longitudinal vortex in a supersonic boundary layer

A. Panina, A. Kosinov, N. Semionov, Yu Yermolaev

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

3 Citations (Scopus)

Abstract

Investigations of the interaction of stationary weak shock waves with a flow in the vicinity of the attachment line at the leading edges of the models and their influence on the laminar-turbulent transition are considered in this paper. The experiments were conducted at Mach 2 and unit Reynolds number Re1 = 8×106 m-1 on the model of a flat steel plate with a sharp leading edge. The sticker placed on the test section wall was applied to induce the pair of weak shock waves. It was found out that in the initial section, the presence of a longitudinal vortex has the greatest effect on the excitation of perturbations at a frequency of 40 kHz, in downstream direction it was detected the appearance of additional peaks in the amplitude spectra over β at frequencies f=1-40 kHz.

Original languageEnglish
Title of host publication19th International Conference on the Methods of Aerophysical Research, ICMAR 2018
Editors Fomin
PublisherAmerican Institute of Physics Inc.
Number of pages4
Volume2027
ISBN (Electronic)9780735417472
DOIs
Publication statusPublished - 2 Nov 2018
Event19th International Conference on the Methods of Aerophysical Research, ICMAR 2018 - Akademgorodok, Novosibirsk, Russian Federation
Duration: 13 Aug 201819 Aug 2018

Publication series

NameAIP Conference Proceedings
PublisherAMER INST PHYSICS
Volume2027
ISSN (Print)0094-243X

Conference

Conference19th International Conference on the Methods of Aerophysical Research, ICMAR 2018
CountryRussian Federation
CityAkademgorodok, Novosibirsk
Period13.08.201819.08.2018

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