Shock-wave/boundary-layer interactions with bleed through rows of holes

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

doi:10.2514/3.24016

Cited by 37 publications

(12 citation statements)

References 14 publications

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“…Although the VG has a promising ability in separation reduction, its intrusion into the flow inevitably induces parasitic drag. The active flow control strategy in the form of ejection/bleeding are non-intrusive to the flow field [9,10] , hence no shape drag will result. However, ejection consumes a considerable amount of the precious pressurized air from the engine, while bleeding removes a good portion of the ingested flow mass.…”

Section: Introductionmentioning

confidence: 99%

Shock wave boundary layer interaction controlled by surface arc plasma actuators

Tian

Sun

et al. 2018

Physics of Fluids

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This is the accepted version of the paper.This version of the publication may differ from the final published version. Permanent repository link: http://openaccess.city.ac.uk/20337/ Link to published version: http://dx. ABSTRACTAn array of 16 surface arc plasma actuators (SAPAs) is employed to control the shock wave boundary layer interaction (SWBLI) at a 26° compression ramp in a Mach 2.0 flow. A new electrical circuit is used to actuate all the 16 SAPAs. The electrical measurement reveals significant augmentation in peak current (200 A) and energy deposition of 1.05 J, which is the nominal characteristics of the setup. The SAPA array is later applied for SWBLI control. The actuator array is placed upstream of the SWBLI and operates at four different frequencies, namely 500 Hz, 1 kHz, 2 kHz and 5 kHz. In the wind tunnel experiment, high-speed schlieren at 25,000 frames per second is used for flow visualization. The shock wave system is modified significantly by the controlling gas blobs (CGBs) generated by SAPAs. The foot portion of the separation shock wave disappears and the oblique shock wave bifurcates when the CGBs passes through the interaction region. The shock weakening effect is further verified through the rms of the schlieren intensity of the same phase.Keywords: shock wave boundary layer interaction, surface arc plasma actuator, supersonic flow control, active flow control a) Electronic mail: wuyun1223@126.com.

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Section: Introductionmentioning

confidence: 99%

Shock wave boundary layer interaction controlled by surface arc plasma actuators

Tian

Sun

et al. 2018

Physics of Fluids

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“…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.…”

mentioning

confidence: 98%

“…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. Given the fact that shock/boundary-layer interactions tend to be unsteady on a large scale, and that local pressure differences can lead to periodic blowing/suction even in active control devices [11], it appears that accounting for the time-dependent nature of the control approach and its interaction with the flow may be critical to achieving better predictions.…”

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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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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“…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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Shock-wave/boundary-layer interactions with bleed through rows of holes

Cited by 37 publications

References 14 publications

Shock wave boundary layer interaction controlled by surface arc plasma actuators

Shock wave boundary layer interaction controlled by surface arc plasma actuators

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

Aerothermal characteristics of bleed slot in hypersonic flows

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