Numerical study of shock-wave/boundary-layer interactions with bleed

Hahn, Todd; Shih, T. I.-P.; Chyu, W. J.

doi:10.2514/3.11698

Cited by 31 publications

(11 citation statements)

References 2 publications

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“…Mach number contours and streamlines in Fig. 14 indicate that the initial entrainment of fluid into the bleed port occurs through a supersonic expansion that is terminated by a barrier shock [8] oriented normal to the flow direction. The lowermost portion of this shock wave interacts with the fluid near the upstream edge of the bleed port, creating a region of separation that acts to reduce the cross-sectional area occupied by the core fluid.…”

Section: A Flat-plate Boundary-layer Simulations With Bleedmentioning

confidence: 94%

“…The design of bleed systems for high-speed inlets is an area in which experimentation and empirical correlations have played a dominant role [3,4]. Most efforts in the simulation of boundary-layer bleed for separation control have concentrated on single slot or hole effects [5][6][7][8], though some studies that consider multiple holes within a periodic array have been reported [9,10]. With the exception of a few three-dimensional studies involving resolution of individual holes using overset-grid [9] or unstructured-mesh [10] techniques, most studies have assumed two-dimensional flow, and all have used Reynolds-averaged NavierStokes (RANS) models or simpler strategies.…”

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confidence: 99%

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Simulation of Shock/Boundary-Layer Interactions with Bleed Using Immersed-Boundary Methods

Ghosh

Choi

Edwards

2010

Journal of Propulsion and Power

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This work uses an immersed-boundary method to simulate the effects of arrays of discrete bleed holes in controlling shock-wave/turbulent-boundary-layer interactions. Both Reynolds-averaged Navier-Stokes and hybrid large-eddy/Reynolds-averaged Navier-Stokes turbulence closures are used with the immersed-boundary technique. The approach is validated by conducting simulations of Mach 2.5 flow over a perforated plate containing 18 individual bleed holes. Computed values of discharge coefficient as a function of bleed plenum pressure are compared to experimental data. Simulations of an impinging-oblique-shock/boundary-layer interaction at Mach 2.45 with and without bleed control are also performed. For the studies with bleed, two different bleed rates are employed. The 68 hole bleed plate is rendered as an immersed object in the computational domain. Wall pressure predictions show that, in general, the large-eddy/Reynolds-averaged Navier-Stokes technique underestimates the upstream extent of axial separation that occurs in the absence of bleed. Good agreement with pitot pressure surveys throughout the interaction region is obtained, however. Flow control at the maximum-bleed rate completely removes the separation region and induces local disturbances in the wall pressure distributions that are associated with the expansion of the boundary-layer fluid into the bleed port and its subsequent recompression. Computed pitot pressure distributions are in good agreement with experiment for the cases with bleed. Swirl-strength probability density distributions are used to estimate the evolution of turbulent length scales throughout the interaction. These, along with Reynolds-stress predictions, indicate that an effect of strong bleed rates is to accelerate the recovery of the boundary layer toward a new equilibrium state downstream of the interaction region. Nomenclature a 1 = model constant for Menter baseline model C f = skin-friction coefficient C M = model constant for mixed-scale model C = model constant for Menter baseline model D = diameter of bleed hole d = distance from nearest-wall/immersed-surface point d ; = normalized distance F 2 = model constant for Menter baseline model f, g = scaling functions G = Heaviside step function based on signed distance function k = turbulent kinetic energy/power law L = length of bleed hole M = Mach number n = coordinate normal to immersed surface P = static pressure P t = pitot pressure Q = sonic flow coefficient or discharge coefficient q 2 = estimate of subgrid kinetic energy R = universal gas constant Re = Reynolds number R n1;l i = residual vector at cell i for time step n 1 and subiteration l r = recovery factor S = characteristic filtered rate of strain T = temperature u = velocity vector, x component of velocity u = friction velocity V = primitive variable vector v = component of velocity in y direction w = component of velocity in z direction X = streamwise distance from leading edge of bleed-plate insert x = streamwise distance from leading edge of computational domain Y = ...

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Section: A Flat-plate Boundary-layer Simulations With Bleedmentioning

confidence: 94%

mentioning

confidence: 99%

Simulation of Shock/Boundary-Layer Interactions with Bleed Using Immersed-Boundary Methods

Ghosh

Choi

Edwards

2010

Journal of Propulsion and Power

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“…Either C or Pb can control the total mass flow rate through the bleeding vent. Hahn et al studied numerically the oblique shock wave/boundary layer interaction with bleed [7] . The configuration is similar to the present study except that the bleeding vent in the present study replaces whole bleeding system including the suction slot and plenum chamber.…”

Section: A P = Pwo -Pomentioning

confidence: 98%

Numerical study on the suppression of shock induced separation on the non-adiabatic wall

Lee

2000

J. of Therm. Sci.

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A numerical model is constructed to simulate the interaction of supersonic ( M = 2.4 ) oblique shock wave / turbulent boundary layer on a strongly heated wall. The heated wall temperature is two times higher than the adiabatic wall temperature and the shock wave is strong enough to induce boundary layer separation. The turbulence model is Spalart-Allmaras model. The comparison of the wall pressure distribution with the experimental data ensures the validity of this numerical model. The effect of strong wall heating enlarges the separation region upstream and downstream. In order to eliminate the separation, wall bleeding is applied at the shock foot position. As a result of the parametric study, the best position of the bleeding slot is selected. The position of the bleeding is very important for the separation suppression. If the bleeding is applied upstream of shock foot, then separation reoccurs after the bleeding slot. If the bleeding is applied downstream of shock foot, the upstream boundary layer is little influenced and still separated. The bleeding vent width is about same as the upstream boundary layer thickness and suction mass flow is 20 to 80 % of the flow rate in the upstream boundary layer. The bleeding mass flow rate is very sensitive to the bleeding vent position if we fix the vent outlet pressure. The final configuration of the shock reflection pattern approaches to the non-viscous value when wall bleeding is applied at the shock impinging point.

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“…Hamed et al [25,26] surveyed the oblique shock wave and laminar boundary layer interaction with bleed. Hahn et al [27], Hamed et al [28][29][30], and Davis and Willis [31] further investigated the oblique shock wave and turbulent boundary layer interaction with bleed through various normal and slanted slots. 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.…”

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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Numerical study of shock-wave/boundary-layer interactions with bleed

Cited by 31 publications

References 2 publications

Simulation of Shock/Boundary-Layer Interactions with Bleed Using Immersed-Boundary Methods

Simulation of Shock/Boundary-Layer Interactions with Bleed Using Immersed-Boundary Methods

Numerical study on the suppression of shock induced separation on the non-adiabatic wall

Aerothermal characteristics of bleed slot in hypersonic flows

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