Joint Experimental and Numerical Approach to Three-Dimensional Shock Control Bump Research

Colliss, SP; Babinsky, Holger; Nübler, Klemens; Lutz, Thorsten

doi:10.2514/1.j052582

Cited by 34 publications

(46 citation statements)

References 17 publications

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“…It is therefore unsurprising that much of the experimental work that has been performed on SCBs has been done using bumps mounted on the floor of small-scale supersonic wind tunnels-notably [6,8,9,12,26,38]. The advantage of this is that the tests are inexpensive, repeatable and concentrate solely on the flow local to the bump, thus enabling a detailed examination.…”

Section: Design Of Experiments For Scb Studiesmentioning

confidence: 99%

“…13 demonstrates this problem with respect to the surface pressure distribution through the shock/boundary layer interaction, which typically has a significantly higher post-shock adverse pressure on an aerofoil than in the wind tunnel experiments. A second area in which the small-scale wind tunnel is likely to be unrepresentative is the state of the boundary layer ahead of the bump, since they are grown in significantly different environments on the wing and in the tunnel, [8]. Finally, there is likely to be significant impact of the wind tunnel aspect ratio, which at best limits the effective bump spacing and at worst introduces unwanted three-dimensionality into the flow.…”

Section: Design Of Experiments For Scb Studiesmentioning

confidence: 99%

“…The data shown are adapted from the study of Bruce et al [7] for a flat plate wind tunnel, and data taken for the same SCB geometry using the wind tunnel set-up of Colliss et al [8]. Whilst the general behaviour of the bump under design conditions is very similar-with the larger values of δ * i , θ i and H i being observed also in the uncontrolled flow-the off-design behaviour is significantly worse in the presence of a streamwise pressure gradient.…”

Section: Shock Positionmentioning

confidence: 99%

“…9c). If such a SCB was installed on a real wing with length of the order of 20-30 % wing chord-a range commonly suggested in literature [10,13]-such variations in [7]; solid light grey lines, SCB using set-up of [8] shock position would correspond to excursions of just 2-4 % of overall wing chord. These numbers suggest that the impact of shock position on SCB performance is a primary concern.…”

Section: Effect Of Flow Conditions On Scb Performancementioning

confidence: 99%

“…Recent work by Colliss et al [8] has defined a joint experimental and computational approach to SCB investigations. By modifying the working section of a blow-down supersonic wind tunnel to increase the post-shock adverse pressure gradient and enable manipulation of the incoming bound- …”

Section: Design Of Experiments For Scb Studiesmentioning

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: Design Of Experiments For Scb Studiesmentioning

confidence: 99%

Section: Design Of Experiments For Scb Studiesmentioning

confidence: 99%

Section: Shock Positionmentioning

confidence: 99%

Section: Effect Of Flow Conditions On Scb Performancementioning

confidence: 99%

Section: Design Of Experiments For Scb Studiesmentioning

confidence: 99%

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Review of research into shock control bumps

Bruce

Colliss

2014

Shock Waves

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Shock/expansion fan interaction with real gas effects for Earth and Mars atmospheric conditions

2022

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Numerical simulations are performed to investigate the real gas effects on shock/expansion fan interaction. Initial perfect gas simulations at low enthalpy capture the flow structures efficiently and outcomes are found to have excellent agreement with the analytical calculations. Furthermore, the simulations with the real gas solver for different enthalpies showed that the variation in enthalpy significantly changes the flow structures. It is observed that an increase in enthalpy leads to a decrease and increase in the postshock and postexpansion fan Mach numbers, respectively. Another important observation is the decrement in the peak pressure ratio with an increment in the enthalpy. These effects are noted to be more pronounced for Mars's environment due to the higher dependency of specific heat on temperature.computational fluid dynamics, Earth and Martian atmospheric simulations, expansion fan, hypersonic flow, real gas flow, shock waves | INTRODUCTIONThe design of high-speed 1,2 aircraft necessitates the appropriate predictions of flow structures associated with it. These flights often encounter shocks and expansion fans. Furthermore, these shock waves and expansion fans may interact with each other. The presence of shock/ expansion fan interaction may complicate the flow structures by affecting the boundary-layer

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