Fifty years of shock-wave/boundary-layer interaction research - What next?

Dolling, D. S.

doi:10.2514/3.14896

Cited by 95 publications

(112 citation statements)

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“…Settles and Dodson 1991). The salient features of this type of interaction can be found in references given by Dolling (2001) and Smits and Dussuage (2006). These studies have shown that when the boundary layer separates, the shock foot and interaction zone undergo an unsteady motion at frequencies much lower than those of the incoming boundary layer.…”

Section: Introductionmentioning

confidence: 99%

Particle image velocimetry measurements of a shock wave/turbulent boundary layer interaction

2007

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Particle image velocimetry is used to investigate the interaction between an incident shock wave and a turbulent boundary layer at Mach 2.1. A particle response assessment establishes the fidelity of the tracer particles.The undisturbed boundary layer is characterized in detail. The mean velocity field of the interaction shows the incident and reflected shock wave pattern, as well as the boundary layer distortion. Significant reversed flow is measured instantaneously, although, on average no reversed flow is observed. The interaction instantaneously exhibits a multi-layered structure, namely, a high-velocity outer region and a low-velocity inner region. Flow turbulence shows the highest intensity in the region beneath the impingement of the incident shock wave. The turbulent fluctuations are found to be highly anisotropic, with the streamwise component dominating. A distinct streamwiseoriented region of relatively large kinematic Reynolds shear stress magnitude appears within the lower half of the redeveloping boundary layer. Boundary layer recovery towards initial equilibrium conditions appears to be a gradual process.

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Section: Introductionmentioning

confidence: 99%

Particle image velocimetry measurements of a shock wave/turbulent boundary layer interaction

2007

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“…Furthermore, maximum mean and fluctuating pressure and thermal loads on a structure are most often found in the regions of shock wave boundary layer interaction (SWBLI) and are thus important factors in vehicle development. Flow control is seen as an important issue in future vehicle design (see Dolling (2001)) requiring a rigorous physical understanding of the mechanisms behind the phenomenon as well as improved simulation capabilities, both of which cannot be attained without fundamental experimental investigations and validation. The renewed attention for the feasibility of sustainable supersonic transport has revived the interest in SWBLI in the moderate supersonic regime.…”

Section: Introductionmentioning

confidence: 99%

Application of a dual-plane particle image velocimetry (dual-PIV) technique for the unsteadiness characterization of a shock wave turbulent boundary layer interaction

Souverein

Oudheusden

Scarano

et al. 2009

Meas. Sci. Technol.

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The unsteady organization and temporal dynamics of the interaction between a planar shock wave impinging on a turbulent boundary layer at a free-stream Mach number of M e = 1.69 is investigated experimentally by means of dual-plane particle image velocimetry (dual-PIV). Two independent PIV systems were combined in a two-component mode to obtain instantaneous velocity fields separated by a prescribed small time delay. This enables us to obtain, in addition to mean and statistical flow properties, also instantaneously time-resolved data to characterize the temporal dynamics of the flow phenomenon in terms of time scales, temporal correlations and convective velocities. The characteristic time scales for the incoming boundary layer, the separation region and the reflected shock are determined by means of the temporal auto-correlation coefficient in the complete flow field for a range of time delays from 5 μs to 2000 μs. These auto-correlation fields are used to quantify the time scales in selected regions of the flow, with special interest for the vortex shedding and the low frequency reflected shock dynamics. This permits resolving the dominant time scales within the boundary layer and the interaction region.

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“…Interactions whereby the adverse pressure gradient is sufficiently strong so as to induce boundary layer separation are particularly complex and typically present large-scale unsteadiness (Dolling 2001;Dupont et al 2005). At high Mach numbers, surface heat transfer rates can be extremely high and often become of primary concern in practical applications involving hypersonic flight (e.g.…”

Section: Introductionmentioning

confidence: 99%

Reattachment heating upstream of short compression ramps in hypersonic flow

Estruch-Samper

2016

Exp Fluids

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Fifty years of shock-wave/boundary-layer interaction research - What next?

Cited by 95 publications

References 0 publications

Particle image velocimetry measurements of a shock wave/turbulent boundary layer interaction

Particle image velocimetry measurements of a shock wave/turbulent boundary layer interaction

Application of a dual-plane particle image velocimetry (dual-PIV) technique for the unsteadiness characterization of a shock wave turbulent boundary layer interaction

Reattachment heating upstream of short compression ramps in hypersonic flow

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