High-resolution PIV measurements of a transitional shock wave-boundary layer interaction

Giepman, Rogier; Schrijer, F.F.J.; Oudheusden, B.W. van

doi:10.2514/6.2014-3333

Cited by 17 publications

(29 citation statements)

References 24 publications

(28 reference statements)

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“…It was noted that the bubble size is approximately halved when increasing the amplitude of the inflow perturbations by a factor of 32 (u inflow /U ∞ = 0.0026 % to 0.082 %). In a recent study by the authors (Giepman, Schrijer & Van Oudheusden 2015) high-resolution particle image velocimetry (PIV) measurements were performed on transitional oblique shock wave reflections for a Mach number of 1.7, unit Reynolds number of 35 × 10 6 m −1 and a flow deflection angle of θ = 3 • (p 3 /p 1 = 1.35). A full-span flat-plate model was used to generate a laminar boundary layer, while a partial-span shock generator was used to position the oblique shock wave in either the laminar, transitional or turbulent part of the boundary layer.…”

Section: Introductionmentioning

confidence: 99%

A parametric study of laminar and transitional oblique shock wave reflections

2018

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High-resolution particle image velocimetry measurements were performed on laminar and transitional oblique shock wave reflections for a range of Mach numbers ($M=1.6{-}2.3$), Reynolds numbers ($Re_{x_{sh}}=1.4\times 10^{6}{-}3.5\times 10^{6}$) and flow deflection angles ($\unicode[STIX]{x1D703}=1^{\circ }{-}5^{\circ }$ or $p_{3}/p_{1}=1.11{-}1.64$). The laminar interactions revealed a long, flat and triangular shaped separation bubble. For relatively strong interactions ($p_{3}/p_{1}>1.2$), the bubble grows linearly in the upstream direction with increasing shock strength. Under these conditions, the boundary layer keeps an on average laminar velocity profile up to the shock impingement location, followed by a quick transition and subsequent reattachment of the boundary layer. For weaker interactions ($p_{3}/p_{1}<1.2$), the boundary layer is able to remain laminar further downstream of the bubble, which consequently results in a later reattachment of the boundary layer. The pressure distribution at the interaction onset for all laminar cases shows excellent agreement with the free-interaction theory, therefore supporting its validity even for incipiently separated laminar oblique shock wave reflections.

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Section: Introductionmentioning

confidence: 99%

A parametric study of laminar and transitional oblique shock wave reflections

2018

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“…Initially developed for low-speed flows, the techniques are now being applied to high-speed SWBLI. Examples of the emerging capabilities of experiments are seen in recent studies of SWBLI by Souverein et al (2010) for turbulent interactions and Giepman et al (2015) for initially laminar interactions. On the numerical side progress has been even more striking, mainly enabled by improvements in computer hardware, but also with careful attention to algorithms, so this is briefly reviewed first, before proceeding to the physical problems.…”

Section: Introductionmentioning

confidence: 99%

Effects of Compressibility and Shock-Wave Interactions on Turbulent Shear Flows

Sandham

2016

Flow Turbulence Combust

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Compressibility effects are present in many practical turbulent flows, ranging from shockwave/boundary-layer interactions on the wings of aircraft operating in the transonic flight regime to supersonic and hypersonic engine intake flows. Besides shock wave interactions, compressible flows have additional dilatational effects and, due to the finite sound speed, pressure fluctuations are localized and modified relative to incompressible turbulent flows. Such changes can be highly significant, for example the growth rates of mixing layers and turbulent spots are reduced by factors of more than three at high Mach number. The present contribution contains a combination of review and original material. We first review some of the basic effects of compressibility on canonical turbulent flows and attempt to rationalise the differing effects of Mach number in different flows using a flow instability concept. We then turn our attention to shock-wave/boundary-layer interactions, reviewing recent progress for cases where strong interactions lead to separated flow zones and where a simplified spanwise-homogeneous problem is amenable to numerical simulation. This has led to improved understanding, in particular of the origin of low-frequency behaviour of the shock wave and shown how this is coupled to the separation bubble. Finally, we consider a class of problems including side walls that is becoming amenable to simulation. Direct effects of shock waves, due to their penetration into the outer part of the boundary layer, are observed, as well as indirect effects due to the high convective Mach number of the shock-induced separation zone. It is noted in particular how shock-induced turning of the detached shear layer results in strong localized 1 damping of turbulence kinetic energy.

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“…For the transitional case, a marginal separation occurs. As part of the TFAST project, Giepman et al [4] reported a similar situation for different SWBLIs at M = 1.7. While the separated region is large for the laminar interaction, for the transitional case the zone of reversed flow is significantly reduced and no meanflow separation is present for the turbulent interaction.…”

Section: Resultsmentioning

confidence: 75%

Transition Location Effect on Oblique Shock-Wave/Boundary-Layer Interaction at M=1.5

Sansica

Sandham

2017

Direct and Large-Eddy Simulation X

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The effect of transition location on the interaction between an oblique shock-wave and a boundary-layer at M = 1.5 on a flat plate is investigated via direct numerical simulations. It is shown that the shock trips transition at the impingement location and the effect of the impingement location on the separation is studied for laminar, transitional and turbulent interactions. Qualitative agreement is obtained with the experiments, as part of the European FP7-2012 TFAST project.

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High-resolution PIV measurements of a transitional shock wave-boundary layer interaction

Abstract: downstream of the shock. Under the same shock conditions, the transitional interaction displays a smaller separation bubble (43δ * i,0 ), and transition is found to be accelerated over the separation bubble.

Cited by 17 publications

References 24 publications

A parametric study of laminar and transitional oblique shock wave reflections

A parametric study of laminar and transitional oblique shock wave reflections

Effects of Compressibility and Shock-Wave Interactions on Turbulent Shear Flows

Transition Location Effect on Oblique Shock-Wave/Boundary-Layer Interaction at M=1.5

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