@inproceedings{b918386d9f3548fc92b44f49004ae29a,
title = "On the oblique breakdown mechanism in a supersonic boundary layer on a swept wing at Mach 2",
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.",
keywords = "STABILITY, TRANSITION, WAVE",
author = "Panina, {A. V.} and Kosinov, {A. D.} and Semionov, {N. V.} and Yermolaev, {Yu G.}",
year = "2017",
month = oct,
day = "26",
doi = "10.1063/1.5007538",
language = "English",
volume = "1893",
series = "AIP Conference Proceedings",
publisher = "American Institute of Physics Inc.",
editor = "Fomin",
booktitle = "Proceedings of the XXV Conference on High-Energy Processes in Condensed Matter, HEPCM 2017",
note = "25th Conference on High-Energy Processes in Condensed Matter, HEPCM 2017 ; Conference date: 05-06-2017 Through 09-06-2017",
}