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TsAGI Science Journal

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ISSN Печать: 1948-2590

ISSN Онлайн: 1948-2604

EXPERIMENTAL INVESTIGATION OF THE SUPERSONIC BOUNDARY LAYER STABILITY ON A SWEPT WING AT MACH NUMBER M = 2

Том 42, Выпуск 1, 2011, pp. 1-12
DOI: 10.1615/TsAGISciJ.v42.i1.10
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Краткое описание

The experimental data of the investigation of stability of a 3D supersonic boundary layer on a swept wing are presented. The experiments are performed on a swept-wing model with a lenticular airfoil, with a swept angle of the leading edge of 45 deg, and at Mach number M = 2. Development of natural disturbances on the model of a thin swept wing is studied in detail on the basis of measurements. The characteristic regions of disturbance development are obtained. The Reynolds number of the region of instability of secondary flow disturbances is experimentally determined. It is shown that the secondary instability of a cross flow plays the main role in a laminar flow transition in the supersonic boundary layer on the swept-wing model.

ЦИТИРОВАНО В
  1. Semionov N. V., Yermolaev Yu. G., Kosinov A. D., Dryasov A. D., Semenov A. N., Yatskikh A. A., The influence of flow parameters on the transition to turbulence in supersonic boundary layer on swept wing, 1770, 2016. Crossref

  2. Kosinov A. D., Kolosov G. L., Semionov N. V., Yermolaev Yu. G., Linear development of controlled disturbances in the supersonic boundary layer on a swept wing at Mach 2, Physics of Fluids, 28, 6, 2016. Crossref

  3. Kosinov Alexander, Semionov Nikolai, Yermolaev Yury, Smorodsky Boris, Kolosov Gleb, Yatskikh Aleksey, Semenov Alexander, The influence of moderate angle-of-attack variation on disturbances evolution and transition to turbulence in supersonic boundary layer on swept wing, Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 234, 1, 2020. Crossref

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