Experimental 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
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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.
Keywords
experiment, supersonic flow, laminar-turbulent transition, turbulence, boundary layer, swept wing
Funding
The work is supported by Russian Foundation for Basic Research (grant No. 19-08-00772). The study was conducted at the Joint Access Center “Mechanics” of ITAM SB RAS
УДК 532.526
Experimental 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
0000-0002-8626-4669 The material was received by the Editorial Board: 05.10.2020
Abstract 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.
Keywords
experiment, supersonic flow, laminar-turbulent transition, turbulence, boundary layer, swept wing
Funding
The work is supported by Russian Foundation for Basic Research (grant No. 19-08-00772). The study was conducted at the Joint Access Center “Mechanics” of ITAM SB RAS
УДК 532.526
Experimental 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 = 2References: Kocharin V. L., Semionov N. V., Kosinov A. D., Yatskikh A. A., Shipul S. A., Yermolaev Yu. G. Experimental 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. Siberian Journal of Physics . 2021, vol. 16, no. 1. P. 44–52. (in Russ.). DOI: 10.25205/2541-9447-2021-16-1-44-52