Three-dimensional shock-wave/boundary-layer interactions with bleed

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

doi:10.2514/3.11854

Cited by 49 publications

(17 citation statements)

References 7 publications

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“…This becomes important when trying to model bleed using boundary conditions where the behavior of turbulence quantities at the boundary must also be defined or source terms used to impose its growth. The general structure of the flow seen here is consistent with other numerical bleed investigations by Manavasi et al [12], Hamed et al [15], Slater [17], and Shih et al [6]. Looking at the x-vorticity contours shown in Fig.…”

Section: Resultssupporting

confidence: 92%

“…As the flow reaches the back side of the bleed hole, a "barrier" shock is formed that then extends up into the freestream. This was also seen by Slater [17], Shih et al [6], and Hamed et al [15]. Inside the bleed hole, the incoming flow is reflected off the back wall of the bleed hole and is then exhausted into the plenum in a complicated, diamond jetlike flow structure.…”

Section: Resultsmentioning

confidence: 61%

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Simulations and Models for Aspiration in a Supersonic Flow Using OVERFLOW

et al. 2015

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Section: Resultssupporting

confidence: 92%

Section: Resultsmentioning

confidence: 61%

Simulations and Models for Aspiration in a Supersonic Flow Using OVERFLOW

et al. 2015

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“…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%

“…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%

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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“…Hamed, et al [13][14][15][16][17][18] and Remlinger, Shin and Chyll [19][20][21][22] followed an alternative approach to investigating bleed effects. They conducted numerical simulations in which the viscous flow field was resolved inside the individual bleed holes and slots.…”

Section: Introductionmentioning

confidence: 99%

Flow characteristics in boundary-layer bleed slots with plenum

Hamed

Yeuan

Jun

1996

Journal of Propulsion and Power

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Numerical simulations were conducted to investigate the performance characteristics of bleed through normal slots and its effect on the turbulent boundary layer development under zero and strong adverse pressure gradient caused by incident oblique shock. The solution to the compressible Navier-Stokes and k-e equations was obtained in a domain that includes the regions inside the bleed slot and plenum in addition to the external flow. The computational results demonstrate the interactions between the plenum, and bleed flow and the effect of incident shock on the boundary layer development downstream.The computed results agree with the experimentally measured pitot and static pressure distribution inside the slot. The bleed mass flow without incident shock was underpredicted over the range of plenum pressures.The computations predicted the measured increase in bleed mass flow with incident shock.

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Three-dimensional shock-wave/boundary-layer interactions with bleed

Cited by 49 publications

References 7 publications

Simulations and Models for Aspiration in a Supersonic Flow Using OVERFLOW

Simulations and Models for Aspiration in a Supersonic Flow Using OVERFLOW

Aerothermal characteristics of bleed slot in hypersonic flows

Flow characteristics in boundary-layer bleed slots with plenum

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