Control of shock-wave/boundary-layer interactions by bleed

Chyu, W. J.; Rimlinger, Mark J.; Shih, T. I.-P.

doi:10.2514/3.12886

Cited by 39 publications

(14 citation statements)

References 10 publications

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“…In a similar timeframe researchers like Benson, et al, 8 Chyu, et al 9 and Shih, et al 10 were simulating bleed holes and looking at the structure of supersonic bleed. Subsequently Li et.…”

Section: B Previous Workmentioning

confidence: 95%

Comparison of Experimental and Computational Flow Structure Investigations of a Normal-Hole Bled Supersonic Boundary Layer

Oorebeek

Babinsky

Ugolotti

et al. 2014

32nd AIAA Applied Aerodynamics Conference

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A series of experiments have been conducted on an array of bleed holes spanning the width of the CUED supersonic wind tunnel at Mach numbers of 1.8 and 2.5. The wind tunnel was run with varying levels of suction, and the resulting flow structure over the bleed array was subsequently mapped with a Laser Doppler Velocimetry (LDV) system at a resolution of 0.25 hole diameters or better. The same wind tunnel setup was also simulated using the OVERFLOW Navier-Stokes equation solver. Overall good agreement was found in the definition of the expansion fan and barrier shock pattern produced by flow entering the normal holes, with the production of streamwise vorticity noted in both CFD and experimental studies. The proposed mechanism of vorticity generation is an effect of the barrier shock standing off from the rear edge of each bleed hole, and is predicted by CFD to increase in strength as Mach number increases, as well as when the vorticity is produced by a single hole, rather than an array. Both studies found that vorticity decreases as suction strength is reduced, however the experimental study showed the vortices persist farther downstream than predicted by CFD.

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“…In a similar timeframe researchers like Benson, et al, 8 Chyu, et al 9 and Shih, et al 10 were simulating bleed holes and looking at the structure of supersonic bleed. Subsequently Li et.…”

Section: B Previous Workmentioning

confidence: 95%

Comparison of Experimental and Computational Flow Structure Investigations of a Normal-Hole Bled Supersonic Boundary Layer

Oorebeek

Babinsky

Ugolotti

et al. 2014

32nd AIAA Applied Aerodynamics Conference

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show abstract

“…Extensive investigations of bleed in supersonic flowfields with and without shock impingement have been conducted to analyze the bleed flow phenomena and its effectiveness in flow control [24][25][26][27][28][29][30][31][32][33][34]. Syberg and Koncsek [24] studied the effects of bleed hole size, slant angle, and length-to-diameter ratio on flow characteristics in the bleed zone without shock impingement.…”

Section: Description Of Flow Phenomena Around the Bleed Interaction Rmentioning

confidence: 99%

“…In their studies, a set of parameters were examined, including bleed mass flow rates, slot location relative to shock impingement point, slot angle, and slot length-to-width ratio. Moreover, Shih, Chyu, and Rimlinger [32][33][34], and Hamed et al [35] numerically characterized three dimensional flow features in the vicinity of bleed holes with shock impingement. Through the aforementioned investigations, several important features of the bleed interaction are identified, as shown in Figure 1.…”

Section: Description Of Flow Phenomena Around the Bleed Interaction Rmentioning

confidence: 99%

Aerothermal characteristics of bleed slot in hypersonic flows

Yue

et al. 2015

Sci. China Phys. Mech. Astron.

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Two types of flow configurations with bleed in two-dimensional hypersonic flows are numerically examined to investigate their aerodynamic thermal loads and related flow structures at choked conditions. One is a turbulent boundary layer flow without shock impingement where the effects of the slot angle are discussed, and the other is shock wave boundary layer interactions where the effects of slot angle and slot location relative to shock impingement point are surveyed. A key separation is induced by bleed barrier shock on the upstream slot wall, resulting in a localized maximum heat flux at the reattachment point. For slanted slots, the dominating flow patterns are not much affected by the change in slot angle, but vary dramatically with slot location relative to the shock impingement point. Different flow structures are found in the case of normal slot, such as a flow pattern similar to typical Laval nozzle flow, the largest separation bubble which is almost independent of the shock position. Its larger detached distance results in 20% lower stagnation heat flux on the downstream slot corner, but with much wider area suffering from severe thermal loads. In spite of the complexity of the flow patterns, it is clearly revealed that the heat flux generally rises with the slot location moving downstream, and an increase in slot angle from 20° to 40° reduces 50% the heat flux peak at the reattachment point in the slot passage. The results further indicate that the bleed does not raise the heat flux around the slot for all cases except for the area around the downstream slot corner. Among all bleed configurations, the slot angle of 40° located slightly upstream of the incident shock is regarded as the best.

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“…Hahn, et al [10] reported a study on bleed through single and multiple slots and examined the effects of spacing between slots, width/depth ratio of slots, and shock strength with focus on the minimum amount of bleed needed to eliminate shock-wave-induced flow separation. Rimlinger, et al [11] and Shih, et al [12] in a study involving bleed through a single normal hole and Chyu, et al [13,14] in a study involving bleed through three holes in tandem showed that bleed of a supersonic boundary layer induced the formation of a "barrier" shock in each hole and described the nature of that shock structure for normal and inclined holes with and without incident shock waves. Rimlinger, et al [15][16][17], in a study involving four rows of bleed holes arranged in a staggered fashion, showed that two rows of staggered normal holes is able to eliminate shock-wave induced flow separation if the two rows are located just upstream of where the shock wave incidents on the boundary layer.…”

Section: Overviewmentioning

confidence: 99%

Control of Shock-Wave/Bound-Layer Interactions by Bleed

Shih

2008

International Journal of Fluid Machinery and Systems

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Bleeding away a part of the boundary layer next to the wall is an effective method for controlling boundary-layer distortions from incident shock waves or curvature in geometry. When the boundary-layer flow is supersonic, the physics of bleeding with and without an incident shock wave is more complicated than just the removal of lower momentum fluid next to the wall. This paper reviews CFD studies of shock-wave/boundary-layer interactions on a flat plate with bleed into a plenum through a single hole, three holes in tandem, and four rows of staggered holes in which the simulation resolves not just the flow above the plate, but also the flow through each bleed hole and the plenum. The focus is on understanding the nature of the bleed process.

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Control of shock-wave/boundary-layer interactions by bleed

Cited by 39 publications

References 10 publications

Comparison of Experimental and Computational Flow Structure Investigations of a Normal-Hole Bled Supersonic Boundary Layer

Comparison of Experimental and Computational Flow Structure Investigations of a Normal-Hole Bled Supersonic Boundary Layer

Aerothermal characteristics of bleed slot in hypersonic flows

Control of Shock-Wave/Bound-Layer Interactions by Bleed

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