SBLI control for wings and inlets

Babinsky, Holger; Ogawa, H.

doi:10.1007/s00193-008-0149-7

Cited by 92 publications

(36 citation statements)

References 20 publications

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“…Such studies are only possible in parallel walled ducts where the incoming (supersonic) Mach number is uniform and set by an upstream throat and the shock position is fixed artificially. Babinsky and co-workers at Cambridge University spent considerable effort developing such a set-up [25] that allowed them to perform studies with SCBs at two discrete Mach numbers: 1.3 and 1.5 [3,6,12,24,26,38] and also a small number of (currently unpublished) tests at Mach 1.4. A common conclusion from these studies was that higher Mach numbers caused greater levels of separation that promoted stronger vortical flow structures in the wakes of 3-D SCBs.…”

Section: Shock Positionmentioning

confidence: 99%

“…It has been demonstrated that the vortical flow structures produced by 3-D SCBs have the potential for exerting localised positive boundary layer control effects on the post-shock boundary layer in experiments and computations [3,6,9,26,38]. This effect has been likened to that of an array of vortex generators, which have been widely used to expand the performance envelopes of low speed wings and supercritical wings alike.…”

Section: -D Scbsmentioning

confidence: 99%

“…Numerous review papers and research projects have made comparisons between SCBs and other (supersonic and transonic) flow control strategies [1,3,33]. A common conclusion amongst these studies and reviews is that 3-D SCBs offer a unique combination of promising performance potential (in terms of drag and/or buffet) and practicality (in terms of ease of installation, cost, weight, etc.)…”

Section: Comparisons With Other Supersonic Flow Control Strategiesmentioning

confidence: 99%

“…This, coupled with the obvious shock control benefits, has lead to the suggestion that the SCB may have an alternative application in controlling the flow in a supersonic engine intake [3]. In this role the SCB would be required to modify the shock/boundary layer interaction such that the downstream flow is more uniform and carries a higher total pressure recovery to the compressor entry than the uncontrolled flow.…”

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: Shock Positionmentioning

confidence: 99%

Section: -D Scbsmentioning

confidence: 99%

Section: Comparisons With Other Supersonic Flow Control Strategiesmentioning

confidence: 99%

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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“…Shock wave reflection and interaction are interesting from both fundamental [1,2] and applied [3,4] points of view. Traditionally the parameters around the point of shock intersection were predicted with the gas being considered as an inviscid fluid, for example, by using t three-shock theory [5].…”

Section: Introductionmentioning

confidence: 99%