Interaction of Microvortex Generator Flow with Ramp-Induced Shock/Boundary-Layer Interactions

Pierce, Adam J.; Qin, Li; Shih, Yusi; Lu, Frank K.; Liu, Chaoqun

doi:10.2514/6.2011-32

Cited by 7 publications

(2 citation statements)

References 30 publications

(29 reference statements)

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“…Micro Ramps (experimental) Pierce et al (57) 2.5 0.5 based on the work by Wu and Martin (51) Minimum H Micro Ramps (experimental) Babinky et al (16) 2.5 0.3, 0.45, 0.6, 0.9 Maximum pressure recovery vortices with the highest strength compared to the smaller device and removed 69% of the flow separation area with respect to the ND case. The impact of increasing the device size was clearly visible in the relative streamwise velocity contours.…”

Section: Discussionmentioning

confidence: 99%

On ramped vanes to control normal shock boundary layer interactions

Lee

Loth

2018

Aeronaut. j.

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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 (0.34δ, 0.52δ and 0·75δ) 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 (0.75δ) 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, wherebyh/δ~1 is often optimum for incompressible flows while higher Mach numbers lead to small optimum heights, tending towards h/δ~0.45 atM=2.5.

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Section: Discussionmentioning

confidence: 99%

On ramped vanes to control normal shock boundary layer interactions

Lee

Loth

2018

Aeronaut. j.

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“…The micro-ramp is a type of micro-vortex generator (MVG), which has been demonstrated as an effective tool in reducing flow separation caused by shock wave/boundary layer interactions (SWBLIs) [1][2][3][4]. In order to establish a better design for the micro-ramp, fundamental studies have been carried out to understand the flow physics around the micro-ramp [5][6][7][8][9][10][11].…”

Section: Introductionmentioning

confidence: 99%

The Vortical Structures in the Rear Separation and Wake Produced by a Supersonic Micro-Ramp

Wang

Yan

Sun

et al. 2014

Flow Turbulence Combust

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This is the accepted version of the paper.This version of the publication may differ from the final published version. Permanent repository link AbstractThe vortical structures in the rear separation and wake region produced by a micro-ramp that immersed in a supersonic turbulent boundary layer are investigated. The small scale separation close to the trailing edge was reveled and this confirms the previous experimental observation. Between the reverse region and surrounding fast moving flow, a three-dimensional shear layer was formed, and vortices are generated. By using vortex line method, the spiral points were understood as the cross-sections of the Ω-shaped vortices that follow the shape of the separation. The vortical structure was analogous to that in the wake region, where similar Ω-shaped vortex can be observed which follows the deficit region caused by the micro-ramp. Finally, the revealed flow topology was conceived beneficial to studying the wall bounded turbulence which involves similar vortical structures but in a smaller scale, while the vortical pattern in the current micro-ramp wake is larger.

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