Large-eddy simulation of passive shock-wave/boundary-layer interaction control

Pasquariello, Vito; Grilli, Muzio; Hickel, Stefan; Adams, Nikolaus A.

doi:10.1016/j.ijheatfluidflow.2014.04.005

Cited by 81 publications

(26 citation statements)

References 37 publications

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“…The separation shock foot penetrates deeply into the incoming TBL, a phenomenon being associated with the high Reynolds number of the flow (Loginov et al 2006;Ringuette et al 2009). As will be discussed later in §3.3, this feature causes a stronger footprint on the fluctuating wall-pressure signal as compared to SWBLI at lower Reynolds number and same Mach number (Adams 2000;Pasquariello et al 2014;Nichols et al 2016). In the same figure the formation of a detached turbulent shear layer originating from the separation shock is visible and contains the separated-flow area.…”

Section: Instantaneous and Mean Flow Organisationmentioning

confidence: 81%

“…The viscous flux is discretised using a 2 nd -order central difference scheme, and the 3 rd -order Runge-Kutta scheme of Gottlieb & Shu (1998) is used for time integration. This numerical method has been successfully applied to a wide range of LES involving shock-turbulence interaction, ranging from canonical test cases ) to SWBLI at a compression-expansion ramp (Grilli et al 2012(Grilli et al , 2013, flow control of SWBLI on a flat plate (Pasquariello et al 2014), shock train in a divergent nozzle (Quaatz et al 2014) and transition analysis between regular and irregular shock patterns of SWBLI (Matheis & Hickel 2015).…”

Section: Governing Equations and Numerical Approachmentioning

confidence: 99%

“…Touber & Sandham (2009) were probably among the first to publish a successful comparison between their long-time (10 4 δ 0 U 0 ) narrow-domain LES results and experimental data with respect to the unsteady shock motion. Further LES studies for impinging SWBLI with a focus on low-frequency aspects of the interaction have been published thereafter (Pirozzoli et al 2010;Hadjadj 2012;Agostini et al 2012;Aubard et al 2013;Morgan et al 2013;Pasquariello et al 2014;Nichols et al 2016). All of these studies, however, predominantly focused on weak interactions (with respect to the absence of a distinct pressure plateau within the separated flow) and/or low Reynolds numbers being typically below Re δ0 ≈ 60 ⋅ 10 3 .…”

Section: Introductionmentioning

confidence: 99%

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Unsteady effects of strong shock-wave/boundary-layer interaction at high Reynolds number

2017

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We analyse the low-frequency dynamics of a high-Reynolds-number impinging shockwave/turbulent boundary-layer interaction (SWBLI) with strong mean-flow separation. The flow configuration for our grid-converged large-eddy simulations (LES) reproduces recent experiments for the interaction of a Mach 3 turbulent boundary layer with an impinging shock that nominally deflects the incoming flow by 19.6○ . The Reynolds number based on the incoming boundary layer thickness of Re δ0 ≈ 203 ⋅ 10 3 is considerably higher than in previous LES studies. The very long integration time of 3805 δ 0 U 0 allows for an accurate analysis of low-frequency unsteady effects. Experimental wallpressure measurements are in good agreement with the LES data. Both datasets exhibit the distinct plateau within the separated-flow region of a strong SWBLI. The filtered three-dimensional flow field shows clear evidence of counter-rotating streamwise vortices originating in the proximity of the bubble apex. Contrary to previous numerical results on compression ramp configurations, these Görtler-like vortices are not fixed at a specific spanwise position, but rather undergo a slow motion coupled to the separationbubble dynamics. Consistent with experimental data, power spectral densities (PSD) of wall-pressure probes exhibit a broadband and very energetic low-frequency component associated with the separation-shock unsteadiness. Sparsity-promoting dynamic mode decompositions (SPDMD) for both spanwise-averaged data and wall-plane snapshots yield a classical and well-known low-frequency breathing mode of the separation bubble, as well as a medium-frequency shedding mode responsible for reflected and reattachment shock corrugation. SPDMD of the two-dimensional skin-friction coefficient further identify streamwise streaks at low frequencies that cause large-scale flapping of the reattachment line. The PSD and SPDMD results of our impinging SWBLI support the theory that an intrinsic mechanism of the interaction zone is responsible for the lowfrequency unsteadiness, in which Görtler-like vortices might be seen as a continuous (coherent) forcing for strong SWBLI.

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Section: Instantaneous and Mean Flow Organisationmentioning

confidence: 81%

Section: Governing Equations and Numerical Approachmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Unsteady effects of strong shock-wave/boundary-layer interaction at high Reynolds number

2017

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“…Hence, controlling the shock-wave induced flow separation is always a focus in SWTBLI researches and many active and passive control approaches have been proposed 11 . Passive control devices include vortex generators [12][13][14] , Mesoflaps [15][16][17] , ventilation duct or porous wall over cavity 18,19 , etc. Active controls using plasma is now gaining more and more attentions in high-speed flows for their advantages of avoiding any ad hoc mechanical components, enabling high effectiveness and ability of high-frequency modulation.…”

Section: Introductionmentioning

confidence: 99%

Large-Eddy Simulation of Shock-Wave/Turbulent Boundary Layer Interaction and Its Control Using Sparkjet

Yang

Yao

Fang

et al. 2016

Int. J. Mod. Phys. Conf. Ser.

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Large-eddy simulation (LES) of an oblique shock-wave generated by an 8°sharp wedge impinging onto a spatially-developing Mach 2.3 turbulent boundary layer and their interactions has been carried out in this study. The Reynolds number based on the incoming flow property and the boundary layer displacement thickness at the impinging point without shock-wave is 20,000. The detailed numerical approaches are described and the inflow turbulence is generated using the digital filter method to avoid artificial temporal or streamwise periodicity. Numerical results are compared with the available wind tunnel PIV measurements of the same flow conditions. Further LES study on the control of flow separation due to the strong shock-viscous interaction is also conducted by using an active control actuator "SparkJet" concept. The single-pulsed characteristics of the control device are obtained and compared with the experiments. Instantaneous flowfield shows that the "SparkJet" promotes the flow mixing in the boundary layer and enhances its ability to resist the flow separation. The time and spanwise averaged skin friction coefficient distribution demonstrates that the separation bubble length is reduced by maximum 35% with the control exerted.

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“…By doing so, the resulting relatively more energetic boundary layer becomes more resistant to conditions imposed by the adverse pressure gradient, which helps to reduce the overall extent of the separation and the associated flow unsteadiness. Present methods of flow control rely primarily on the use of boundary-layer suction [11][12][13] or bleed [14] systems wherein the decelerating or retarded boundary layer is either removed (suction) by replacing it with a new, thinner, one or its growth is influenced by adding mass flow into it (bleed). Although these methods are very effective and have found several hardware applications, their associated systems are quite complex.…”

Section: Introductionmentioning

confidence: 99%