Published 6 issues per year
ISSN Print: 1948-2590
ISSN Online: 1948-2604
FORMATION OF STREAMWISE VORTICES BEHIND THE LINE OF SUPERSONIC SEPARATED FLOW REATTACHMENT AT A COMPRESSION CORNER
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.
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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
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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
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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
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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