Microramps Upstream of an Oblique-Shock/Boundary-Layer Interaction

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To examine the potential of micro vortex generators for shock/boundary-layer interaction control, a detailed experimental and computational study in a supersonic boundary laver at M = 3.0 was undertaken. The experiments employed a flat-plate boundary layer with an impinging oblique shock with downstream total-pressure measurements. The moderate Reynolds number of 3800 allowed the computations to use monotone-integrated large eddy simulations. The monotone-integrated large eddy simulations predictions indicated that the shock changes the structure of the turbulent eddies and The primary vortices generated from the microramp. Furthermore, they generally reproduced the experimentally obtained mean velocity profiles, unlike similarly resolved Reynoldsaveraged Navier-Stokes computations. The experiments and monotone-integrated large eddy simulations results indicate that the microramps, for which the height is h approximate to 0.5 delta, can significantly reduce boundary-layer thickness and improve downstream boundary-layer health as measured by the incompressible shape function H. Regions directly behind the ramp centerline tended to have increased boundary-layer thickness, indicating the significant three-dimensionality of the flowfield. Compared with baseline sizes, smaller microramps yielded improved total-pressure recovery. Moving the smaller ramps closer to the shock interaction also reduced the displacement thickness and the separated area. This effect is attributed to decreased wave drag and the closer proximity of the vortex pairs to the wall.
Publisher
AMER INST AERONAUTICS ASTRONAUTICS
Issue Date
2010-01
Language
English
Article Type
Article; Proceedings Paper
Citation

AIAA JOURNAL, v.48, no.1, pp.104 - 118

ISSN
0001-1452
DOI
10.2514/1.41776
URI
http://hdl.handle.net/10203/272994
Appears in Collection
AE-Journal Papers(저널논문)
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