Open AccessExperimental Study of the Influence of Unit Reynolds Number on the Laminar-Turbulent Transition on the Model Swept Wing with a Subsonic Leading Edge at M = 2
Author(s) -
V. L. Kocharin,
Н. В. Семёнов,
А. Д. Косинов,
A. A. Yatskikh,
S. A. Shipul,
Yury G. Yermolaev
Publication year - 2021
Publication title -
sibirskij fizičeskij žurnal
Language(s) - English
Resource type - Journals
ISSN - 2541-9447
DOI - 10.25205/2541-9447-2021-16-1-44-52
Subject(s) - laminar flow , boundary layer , leading edge , reynolds number , swept wing , turbulence , supersonic speed , laminar turbulent transition , mechanics , wing , mach number , physics , angle of attack , flow separation , aerodynamics , thermodynamics
Experimental studies of the influence of unit Reynolds number on the laminar-turbulent transition in a supersonic boundary layer of a swept wing with a subsonic leading edge at Mach number 2 are performed. The experiments were performed on a model of a swept wing with a swept angle of the leading edge of 72 degrees and with a 3% profile with a variable chord length in span. The hot-wire measurements showed that a laminar-turbulent transition in a supersonic boundary layer of a swept wing with a subsonic leading edge occurs earlier (~25-30%) than on a model with a supersonic leading edge with the same oncoming flow parameters. It is shown that a change unit Reynolds number insignificant influence the laminar-turbulent transition in the boundary layer of a swept wing with a subsonic leading edge.