Impact of Ramped Vanes on Normal Shock Boundary-Layer Interaction

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Large-eddy simulations of a vortex generator embedded upstream of a normal shock boundary-layer interaction followed by a subsonic diffuser were conducted. In particular, the ""ramped-vane"" flow control device was placed in a supersonic boundary layer with a freestream Mach number of 1.3 and a Reynolds number of 2400 based on momentum thickness. The ramped vane had a height of 0.52 delta and generated strong streamwise vorticity that entrained the high-momentum flow to the near-wall region. This contributed to decreasing the shock-induced flow separation while significantly increasing the skin friction coefficient in the diffuser where a strong adverse pressure gradient was present. In addition, it was found that the high-momentum flow persisted far downstream of the shock interaction region, which yielded reductions of both the displacement thickness and the shape factors compared to the uncontrolled case.
Publisher
AMER INST AERONAUTICS ASTRONAUTICS
Issue Date
2012-10
Language
English
Article Type
Article
Citation

AIAA JOURNAL, v.50, no.10, pp.2069 - 2079

ISSN
0001-1452
DOI
10.2514/1.J051253
URI
http://hdl.handle.net/10203/272870
Appears in Collection
AE-Journal Papers(저널논문)
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