Shock Wave/Boundary-Layer Interaction Control Using a Combination of Vortex Generators and Bleed

Titchener, Neil; Babinsky, Holger

doi:10.2514/1.j052079

Cited by 74 publications

(45 citation statements)

References 30 publications

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“…However, further insight into the flow physics and a more intake-neutral analysis is required to assess the potential of SCBs in this regard more fully. One useful way in which this might proceed is to follow the approach of Titchener et al [37], who defined a simplified canonical intake flow in a blowdown supersonic wind tunnel and used it to study various configurations of vortex generators. The simplest metric of performance in these tests would be the degree to which the bumps can suppress (or reduce) boundary layer separation.…”

Section: Scbs In Intakesmentioning

confidence: 99%

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Review of research into shock control bumps

Bruce

Colliss

2014

Shock Waves

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This paper presents a review of research on shock control bumps (SCBs), a class of flow control device with potential for application to transonic wings. Beginning with a brief review of the origins of the SCB concept, the primary focus is on the more recent studies from the last decade. Results from both experimental and numerical work are considered and the synergy between these two approaches to SCB research is critically explored. It is shown that the aerodynamic performance enhancement potential of SCBs, namely their capacity for drag reduction and delaying the onset of buffet for transonic wings, has been widely demonstrated in the literature, as has the high sensitivity of SCB performance to flow conditions including shock strength and position, and post-shock adverse pressure gradient. These characteristic features of SCBs are relatively well explained in terms of the flow physics that have been observed for different bump geometries. This stems from a number of studies that have focused on the balance of viscous and inviscid flow features and also the mechanism by which finite span SCBs generate streamwise vorticity. It is concluded that our understanding of SCBs is reaching an advanced level of maturity for SCBs in simple configurations and steady flow fields. However, SCB performance in unsteady flow and on swept wings requires further investigation before the concept can be considered a viable candidate for transonic wings. These investigations should adopt a multi-disciplinary approach combining carefully designed experiments and targeted computations. Finally, two concepts for future SCB research are suggested: the adaptive SCB and SCBs in engine intakes.Communicated by A. Hadjadj.

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Section: Scbs In Intakesmentioning

confidence: 99%

“…This could be measured either by direct means (surface oil flow visualisation) or via surface pressure distributions. Additionally, following [37], the total pressure downstream at the simulated aerodynamic interface plane (AIP) could serve as a measure of the flow distortion in the viscous region.…”

Section: Scbs In Intakesmentioning

confidence: 99%

Review of research into shock control bumps

Bruce

Colliss

2014

Shock Waves

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“…They discussed that, the LES is able to predict the complex flow within the pseudo-shock system reliably and accurately. In addition, a few researchers have examined the controlling conditions of the flow behavior with shock waves [18][19][20][21][22].…”

Section: Introductionmentioning

confidence: 99%

Three dimensional CFD investigation of shock train structure in a supersonic nozzle

2015

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“…Passive control approaches such as cavities [10], vortex generators [11][12][13], micro-ramps [14], and strakes [15] are effective in reducing SWBLI unsteadiness; however, these approaches are effective only in limited operational condition and can cause unfavorable effects in off-design operation. Active control approaches such as energy deposition [16,17] and jet injection [18,19] can widen the effective operational ranges because the operational conditions can be tuned to the flow conditions.…”

Section: Introductionmentioning

confidence: 99%

Suppression of Low-Frequency Shock Oscillations over Boundary Layers by Repetitive Laser Pulse Energy Deposition

et al. 2016

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Abstract:The effect of repetitive energy deposition on low Strouhal number oscillations of the shock wave induced by boundary-layer interaction over a cylinder-flare model was studied. The fluctuation of the energy deposition frequency was induced in the flow, because the bubble generated by the energy deposition flowed downstream along the surface repeatedly. The region before the bubble size was affected by the energy deposition directly, so the fluctuation frequency was equal to the energy deposition frequency. However, the flare shock behavior at a position farther from the surface than the bubble size was also affected strongly by the energy deposition. For low-frequency unsteadiness and the effect of energy deposition on its unsteadiness, two categories have been observed. In the relatively small flare angle case, the flare shock was oscillated owing to the fluctuation induced by the boundary-layer interaction at the shock foot, and its oscillation occurred at 2.1 kHz with a small amplitude. The amplitude of this oscillation was decreased by highly repetitive energy depositions, and its amplitude could not be detected at a highly repetitive energy deposition. In the longer cylinder section case, the region of the shock-wave interaction was widened, and the amplitude of the flare shock oscillation was increased. In this case, the amplitude drastically decreased because of energy deposition.

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Shock Wave/Boundary-Layer Interaction Control Using a Combination of Vortex Generators and Bleed

Cited by 74 publications

References 30 publications

Review of research into shock control bumps

Review of research into shock control bumps

Three dimensional CFD investigation of shock train structure in a supersonic nozzle

Suppression of Low-Frequency Shock Oscillations over Boundary Layers by Repetitive Laser Pulse Energy Deposition

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