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FORMATION OF STREAMWISE VORTICES BEHIND THE LINE OF SUPERSONIC SEPARATED FLOW REATTACHMENT AT A COMPRESSION CORNER

Volume 47, Issue 3, 2016, pp. 267-281
DOI: 10.1615/TsAGISciJ.2016018291
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ABSTRACT

The three-dimensional flow field structure in the area of reattachment of laminar-separated flow at a compression corner is considered. The Mach number of the free stream is M = 6. The model under consideration represents a plate with a sharp leading edge and a ramp installed at 30°. The model width is equal to the length of the plate from the leading edge to the ramp. The formation of streamwise near-wall vortices is discussed based on the results of analysis of the three-dimensional flow vortex structure in the area of reattachment.

CITED BY
  1. Zapryagaev V I, Kavun I N, Trubitsyna L P, Effect of Mach and Reynolds numbers on the parameters of the high-pressure layer in the supersonic separated flow near a ramp, Journal of Physics: Conference Series, 1404, 2019. Crossref

  2. Zapryagaev V I, Kavun I N, Trubitsyna L P, Heat transfer in supersonic separated flow of the compression corner, Journal of Physics: Conference Series, 1382, 1, 2019. Crossref

  3. Trubitsyna L P, Zapryagaev V I, Kavun I N, Effect of side walls on the supersonic ramp flow structure, Journal of Physics: Conference Series, 1404, 1, 2019. Crossref

  4. Zapryagaev V. I., Kavun I. N., Trubitsyna L. P., Structure of a supersonic separated flow over a compression corner with side walls, INTERNATIONAL CONFERENCE ON THE METHODS OF AEROPHYSICAL RESEARCH (ICMAR 2020), 2351, 2021. Crossref

  5. Zapryagaev Valeriy I, Kavun Ivan N, Trubitsyna Lukeriya P, Dynamic layer formation in the reattachment zone for a supersonic laminar separated flow, Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 236, 3, 2022. Crossref

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