Experimental investigation into Parameters Governing Corner Interactions for Transonic Shock-Wave/Boundary-Layer Interactions

Burton, D. M. F.; Babinsky, Holger; Bruce, Paul J.

doi:10.2514/6.2010-871

Cited by 19 publications

(12 citation statements)

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“…Interestingly, the M ∞ = 1.4 data point (attached flow) from Burton et al (2010) lies very slightly below the dashed line in figure 4, suggesting that it may be sensitive to manipulations of the corner flow-field. In practice, any reduction of the corner flow separation should push the test case towards the domain where flow separation in the centre is observed.…”

Section: Review Of Factors Affecting Separation In Normal Sblismentioning

confidence: 92%

“…The results from a number of experimental studies are plotted in figure 3 against Re θ and H i0 . In addition to the results from figure 2, data are also included from tests by Burton, Babinsky & Bruce (2010) and Chriss et al (1989). The latter of these two is particularly noteworthy because they found that the boundary layer along the tunnel centreline remained attached through a M ∞ = 1.59 SBLI in a confined channel.…”

Section: Review Of Factors Affecting Separation In Normal Sblismentioning

confidence: 99%

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Corner effect and separation in transonic channel flows

et al. 2011

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An investigation into parameters affecting separation in normal shock wave/boundary layer interactions (SBLIs) has been conducted. It has been shown that the effective aspect ratio of an experimental facility (defined as δ * /tunnel width) is a critical factor in determining when shock-induced separation will occur. Experiments examining M ∞ = 1.4 and 1.5 normal shock waves in a wind tunnel with a small rectangular cross-section have been performed and show that a link exists between the extent of shock-induced separation on the tunnel centre-line and the size of corner-flow separations. In tests where the corner-flows were modified ahead of the shock (through suction and vortex generators), the extent of separation around the tunnel centre-line was seen to vary significantly. These observations are attributed to the way corner flows modify the three-dimensional shock-structure and the impact this has on the magnitude of the adverse pressure gradient experienced by the tunnel wall boundary layers.

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Section: Review Of Factors Affecting Separation In Normal Sblismentioning

confidence: 92%

Section: Review Of Factors Affecting Separation In Normal Sblismentioning

confidence: 99%

Corner effect and separation in transonic channel flows

et al. 2011

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“…However, recent research has shown that even the 2-D region, specifically the severity of the separation, is affected by the overall three-dimensionality of the interaction. 30 Secondly, separation is clearly visible in all three of the interaction strengths. Thirdly, the most noticeable change between the three cases is the two-dimensionality of the 2-D region.…”

Section: Surface Oil Flow Visualizationmentioning

confidence: 98%

Supersonic Inlet Flow Control Using Localized Arc Filament Plasma Actuators

Samimy¹,

Webb²,

Clifford³

2011

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information Unlimited.Shock Wave/Boundary Layer Interactions (SWBLIs) occur in many applications of interest to the U.S. Air Force and could pose significant problems depending on the specific application. This study has undertaken to investigate the use of ). This frequency is similar to that at which the reflected shock oscillates in unforced SWBLIs. Therefore, LAFPAs are believed to manipulate the natural instability associated with the reflected shock oscillation. The success of the preliminary experiments motivated the design of a new, larger, more flexible facility that utilize a Variable Angle Wedge (VAW) (rather than a compression ramp) to generate the impinging shock wave for SWBLI. This facility is capable of easily generating a wide range of SWBLI strengths, but was found to be a poor environment for testing the LAFPAs control authority due to its inability to modify the LAFPA location. The necessary modifications to add this capability to the facility have been performed. This research is currently continuing with the focus on investigating the actuation authority and mechanism at various SWBLI strengths as well as on the optimization of the control authority.

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“…The flow is also closely symmetric. This lack of shock-induced separation at this relatively high Mach number is discussed in detail by Burton et al [11] and is thought to be a result of three-dimensional effects. Agreement between the surface-flow visualizations obtained in position 1 and in a configuration without a diffuser is evidence that the diffuser is too far downstream to have any significant detrimental effect in the interaction region itself.…”

Section: Uncontrolled Interactionsmentioning

confidence: 65%

Microvortex Generators Applied to a Flowfield Containing a Normal Shock Wave and Diffuser

Titchener

Babinsky

2011

AIAA Journal

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The flow through a terminating shock wave and the subsequent subsonic diffuser typically found in supersonic inlets has been simulated using a small-scale wind tunnel. Experiments have been conducted at an inflow Mach number of 1.4 using a dual-channel working section to produce a steady near-normal shock wave. The setup was designed so that the location of the shock wave could be varied relative to the diffuser. As the near-normal shock wave was moved downstream and into the diffuser, an increasingly distorted, three-dimensional, and separated flow was observed. Compared with the interaction of a normal shock wave in a constant area duct, the addition of the diffuser resulted in more prominent corner interactions. Microvortex generators were added to determine their potential for removing flow separation. Although these devices were found to reduce the extent of separation, they significantly increased three-dimensionality and even led to a large degree of flow asymmetry in some configurations.

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Experimental investigation into Parameters Governing Corner Interactions for Transonic Shock-Wave/Boundary-Layer Interactions

Cited by 19 publications

References 1 publication

Corner effect and separation in transonic channel flows

Corner effect and separation in transonic channel flows

Supersonic Inlet Flow Control Using Localized Arc Filament Plasma Actuators

Microvortex Generators Applied to a Flowfield Containing a Normal Shock Wave and Diffuser

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