Crossflow effects on shock wave/turbulent boundary layer interactions

Renzo, Mario Di; Oberoi, Nikhil; Larsson, Johan; Pirozzoli, Sergio

doi:10.1007/s00162-021-00574-y

Cited by 14 publications

(9 citation statements)

References 33 publications

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“…As shown in previous studies (Di Renzo et al. 2022; Larsson et al. 2022), the presence of a non-zero sweep angle yields substantial enlargement of the interaction zone, as compared to the case of two-dimensional, non-swept interactions.…”

Section: Discussionsupporting

confidence: 50%

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On low-frequency unsteadiness in swept shock wave–boundary layer interactions

et al. 2023

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We derive a scaling law for the characteristic frequencies of wall pressure fluctuations in swept shock wave/turbulent boundary layer interactions in the presence of cylindrical symmetry, based on analysis of a direct numerical simulations database. Direct numerical simulations in large domains show evidence of spanwise rippling of the separation line, with typical wavelength proportional to separation bubble size. Pressure disturbances around the separation line are shown to be convected at a phase speed proportional to the cross-flow velocity. This information is leveraged to derive a simple model for low-frequency unsteadiness, which extends previous two-dimensional models (Piponniau et al., J. Fluid Mech., vol. 629, 2009, pp. 87–108), and which correctly predicts growth of the typical frequency with the sweep angle. Inferences regarding the typical frequencies in more general swept shock wave/turbulent boundary layer interactions are also discussed.

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Section: Discussionsupporting

confidence: 50%

“…The flow set-up replicates that used in previous studies aimed at establishing the effects of cross-flow on SBLIs (Gross & Fasel 2016; Lee & Gross 2021; Di Renzo et al. 2022; Larsson et al. 2022), as sketched in figure 1.…”

Section: Computational Set-upmentioning

confidence: 99%

On low-frequency unsteadiness in swept shock wave–boundary layer interactions

et al. 2023

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“…Using a very large database of experimental and simulation results, these authors catalog unsteady phenomena on the basis of frequency bands and describe qualitative differences between two-dimensional, axisymmetric, open three-dimensional separation in the absence of sidewalls, as well as the effect of the latter on the proposed characterization. Di Renzo, Oberoi, Larsson and Pirozzoli [20] use DNS to address the fundamental problem of shock wave/turbulent boundary layer interaction in the presence of three-dimensionality induced by crossflow. In line with predictions of earlier high-fidelity DNS work [29], these authors find an augmentation of the (mean) size of the separation bubble, associated by changes in the mean flow direction.…”

Section: Summary Of Articles In This Special Issuementioning

confidence: 99%

Special issue on the fluid mechanics of hypersonic flight

Theofilis

Pirozzoli

Martin

2022

Theor. Comput. Fluid Dyn.

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Flow phenomena on maneuverable vehicles that fly at hypersonic speeds and altitudes that reach the Earth's upper stratosphere and lower mesosphere pose challenges that collectively form one of the present-day research frontiers of Fluid Mechanics. Research agencies around the world have realized the multiple benefits derived from transitioning a deeper understanding of hypersonic flow phenomena to actual flying platforms, and support for hypersonic research has increased substantially in the last decade. The result can be seen in Fig. 1, showing the distribution over years and originating countries of a total of 26,300 peer-reviewed research papers that have been published since the word hypersonic first appeared in the literature in the early 1940s and have this word in their title. Early peak activity subsided after the Moon landing, but soon picked up in the early 80s and again around the turn of the century, growing monotonically to the present day. As also shown in Fig. 1, a breakdown by country of origin reveals that two-thirds of the total number of hypersonic publications originate from the USA and China, giving rise to concerns raised by strategic think-tanks [57] and policy advisers [61] regarding potential misuse of hypersonic technology.Hypersonic research has not always come to the limelight on account of potential strategic conflicts. The high plateau in number of papers published around the 1990s, shown in the left plate of Fig. 1, corresponds to intense activity that took place on the crest of the success of the early Space Shuttle flights, relating to the new Orient Express [47] of hypersonic travel. Large (and largely drawing board) projects involving substantial research into hypersonic flow physics, namely the National Aerospace Plane in the USA, Buran in the final years of the Soviet Union, HOTOL in the UK, Hermes in France and Sänger in Germany, alongside lower-scale efforts in India and Brazil, all testified to a time of optimism regarding hypersonic travel in a civilian transport V. Theofilis

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“…Mainly three types of phenomena have been identified. When the upstream boundary layer is turbulent and the SWBLI weak (incipient separated zone), streaks from the upstream boundary layer and associated with longitudinal vortices can interact with the shock system (Ganapathisubramani et al 2007;Ganapathisubramani, Clemens & Dolling 2009;Di Renzo et al 2022). However, when the SWBLI is strong enough to generate a significant separated zone, the latter can induce a streamline curvature of the boundary layer and initiate a centrifugal Görtler-like instability (Pasquariello, Hickel & Adams 2017;Zhuang et al 2018).…”

Section: Introductionmentioning

confidence: 99%

“…2007; Ganapathisubramani, Clemens & Dolling 2009; Di Renzo et al. 2022). However, when the SWBLI is strong enough to generate a significant separated zone, the latter can induce a streamline curvature of the boundary layer and initiate a centrifugal Görtler-like instability (Pasquariello, Hickel & Adams 2017; Zhuang et al.…”

Section: Introductionmentioning

confidence: 99%

Low-frequency resolvent analysis of the laminar oblique shock wave/boundary layer interaction

et al. 2022

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Resolvent analysis is used to study the low-frequency behaviour of the laminar oblique shock wave/boundary layer interaction (SWBLI). It is shown that the computed optimal gain, which can be seen as a transfer function of the system, follows a first-order low-pass filter equation, recovering the results of Touber & Sandham (J. Fluid Mech., vol. 671, 2011, pp. 417–465). This behaviour is understood as proceeding from the excitation of a single stable, steady global mode whose damping rate sets the time scale of the filter. Different Mach and Reynolds numbers are studied, covering different recirculation lengths $L$ . This damping rate is found to scale as $1/L$ , leading to a constant Strouhal number $St_{L}$ as observed in the literature. It is associated with a breathing motion of the recirculation bubble. This analysis furthermore supports the idea that the low-frequency dynamics of the SWBLI is a forced dynamics, in which background perturbations continuously excite the flow. The investigation is then carried out for three-dimensional perturbations for which two regimes are identified. At low wavenumbers of the order of $L$ , a modal mechanism similar to that of two-dimensional perturbations is found and exhibits larger values of the optimal gain. At larger wavenumbers, of the order of the boundary layer thickness, the growth of streaks, which results from a non-modal mechanism, is detected. No interaction with the recirculation region is observed. Based on these results, the potential prevalence of three-dimensional effects in the low-frequency dynamics of the SWBLI is discussed.

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Crossflow effects on shock wave/turbulent boundary layer interactions

Cited by 14 publications

References 33 publications

On low-frequency unsteadiness in swept shock wave–boundary layer interactions

On low-frequency unsteadiness in swept shock wave–boundary layer interactions

Special issue on the fluid mechanics of hypersonic flight

Low-frequency resolvent analysis of the laminar oblique shock wave/boundary layer interaction

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