On ramped vanes to control normal shock boundary layer interactions

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A novel vortex generator design positioned upstream of a normal shock followed by a subsequent diffuser was investigated using large eddy simulations. In particular, ""ramped-vane"" flow control devices with three different heights relative to the incoming boundary layer thickness (0.34 delta, 0.52 delta and 0.75 delta) were placed in a supersonic boundary layer with a freestream Mach number of 1.3 and a Reynolds number of 2400 based on the momentum thickness. This is the first numerical study to investigate the size effect of the ramped-vane for flow control device in terms of shape factor, flow separation and flow unsteadiness. The results showed that these devices generated strong streamwise vortices that entrained high-momentum fluid to the near-wall region and increased turbulent mixing. The devices also decreased shock-induced flow separation, which resulted in a higher downstream skin friction in the diffuser. In general, the largest ramped-vane (0.75 delta) produced the largest reductions in flow separation, shape factor and overall unsteadiness. These results and a careful review of the literature study also determined the quantitative correlation of optimum VG height with Mach number, whereby h/delta similar to 1 is often optimum for incompressible flows while higher Mach numbers lead to small optimum heights, tending towards h/delta similar to 0.45 at M = 2.5.
Publisher
CAMBRIDGE UNIV PRESS
Issue Date
2018-10
Language
English
Article Type
Article
Citation

AERONAUTICAL JOURNAL, v.122, no.1256, pp.1568 - 1585

ISSN
0001-9240
DOI
10.1017/aer.2018.88
URI
http://hdl.handle.net/10203/272666
Appears in Collection
AE-Journal Papers(저널논문)
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