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

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 spanwis...

Full description

Saved in:
Bibliographic Details
Main Authors: Panina, A. V., Kosinov, A. D., Semionov, N. V., Yermolaev, Yu. G.
Format: Conference Proceeding
Language:English
Subjects:
Boundary layer
Breakdown
Fluid dynamics
Fluid flow
Resonant frequencies
Reynolds number
Supersonic boundary layers
Swept wings
Online Access:Get full text
Tags: Add Tag
No Tags, Be the first to tag this record!
Description
Summary: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.
ISSN:0094-243X
1551-7616
DOI:10.1063/1.5007538