Comparison of Bleed and Micro-Vortex Generator Effects on Supersonic Boundary-Layers

This is the accepted version of the paper.This version of the publication may differ from the final published version. Permanent AbstractThe implicitly implemented large eddy simulation (LES) with fifth order WENO scheme by solving the Naiver-Stokes equations was carried out to explore the origin of the momentum deficit caused by a supersonic micro-ramp at flow conditions of Ma=2.5 and Reθ=5760. The numerical results were validated by qualitative and quantitative comparisons with existing experimental data. After describing the aerodynamic properties of the supersonic wake, such as the deficit and the streamwise vortices, the momentum deficit was later detected to originate from the lower portion of the upstream boundary layer while the high momentum fluid near the wall from the upper portion. The position alternation trigged by the microramp was finally proposed as a revised mechanism.

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“…A sharp eye would detect a small region of negative v below the central upwash. Such a region is also measured in the experiment [18] .…”

Section: The Cross Flow Structurementioning

confidence: 80%

“…A cross flow section at x/h=5 is extracted from the averaged flow field, so that qualitative comparison with the LDV measurement of Oorebeek et al [18] can be made. In the u-contour in figure 7(a), the momentum deficit is clearly resolved.…”

Section: The Cross Flow Structurementioning

confidence: 99%

LES investigation into the generation of momentum deficits in the supersonic wake of a micro-ramp

et al. 2014

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“…Comparisons of different passive concepts have also been tested: for example, Ref. [166] assesses bleed versus micro-vortex generators on boundary layers by examining their effects on the shape parameter and skin friction. The effectiveness of combinations of bleed and vortex generators to address the corner flow and the central nominal 2-D SBLI has been presented in Ref.…”

Section: Controlmentioning

confidence: 99%

Progress in shock wave/boundary layer interactions

Gaitonde

2015

Progress in Aerospace Sciences

500

126

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“…In the past, several researchers investigated the effect of porous bleed experimentally. In contrast to real applications, the porous bleed regions in experiments are scaled in size, and only a small number of rows [1][2][3][4][5][6][7], or even a single hole [8][9][10], is investigated. Moreover, the porous bleed is only globally regarded, which means that only little information about the flow in the individual holes exists [11,12].…”

Section: Fig 1 Schematic Of the Flow Through A Porous Plate In Supers...mentioning

confidence: 99%

Parameter Influence on the Porous Bleed Performance with & without Shock-Boundary Layer Interaction

Giehler

Grenson

Bur

2022

AIAA AVIATION 2022 Forum

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Porous bleed systems are a common technique to control shock-boundary layer interactions and/or supersonic boundary layer. However, the influence of various design parameters is still unknown. Even though bleed models are required to minimize the costs of the design process, they often do not include parameter effects. In the present study, the effect of the hole diameter, the porosity level, and the length-to-diameter ratio are investigated by means of three-dimensional RANS simulations. The findings show an influence of the hole diameter on both flow control and efficiency of the porous bleed. A significant impact of the porosity level on the effective control of the shock-boundary layer interaction is found. In contrast, the length-to-diameter ratio does not influence the effective control but affects the efficiency of the system.

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Comparison of Bleed and Micro-Vortex Generator Effects on Supersonic Boundary-Layers

Cited by 8 publications

References 16 publications

LES investigation into the generation of momentum deficits in the supersonic wake of a micro-ramp

LES investigation into the generation of momentum deficits in the supersonic wake of a micro-ramp

Progress in shock wave/boundary layer interactions

Parameter Influence on the Porous Bleed Performance with & without Shock-Boundary Layer Interaction

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