Some Turbulence Characteristics Downstream a Shock Wave - Boundary Layer Interaction

Deleuze, J.; Elena, M.

doi:10.1007/978-94-009-0297-8_123

Cited by 3 publications

(4 citation statements)

References 1 publication

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“…The recirculation zone, characterized by very high levels of fluctuations, extends over the whole interaction zone (0 < X * < 1). Above this region, the mean and turbulent velocity profiles are strongly modified (Deleuze & Elena 1996). The mean velocity profiles have a quasi-linear behaviour in the region 0.1 < y/δ 0 < 1.2, and a second maximum of turbulence appears far from the wall (around y/δ 0 ≈ 0.6) and is still preseved far downstream of the reattachment point.…”

Section: Organization Of the Interactionmentioning

confidence: 95%

“…In addition to compression ramps, a second experimental configuration is the reflection of an incident shock wave impinging on the boundary layer. The mean fields, although less well documented than for the compression ramp case, have been obtained for a wide range of configurations (Chapman, Kuehn & Larson 1957;Hakkinen, Greber & Trilling 1959;Green 1970;Delery & Marvin 1986;Deleuze & Elena 1996;Laurent 1996;Garnier & Sagaut 2002). On the other hand, unsteadiness properties are less well documented for this configuration.…”

Section: Introductionmentioning

confidence: 91%

“…Laser-Doppler anemometry (LDA) measurements of velocity fluctuations have been carried out by Deleuze (1995) and Deleuze & Elena (1996). The Morkovin's representation takes into account density variation in the scaling of Reynolds stresses and good agreement has been found between supersonic and subsonic flow profiles obtained by Klebanoff (1954).…”

Section: Incoming Conditions: the Upstream Boundary Layermentioning

confidence: 99%

“…In the following sections, we will present detailed experimental results in a turbulent boundary layer at a Mach number of 2.3 impinged by an oblique shock wave, with flow deflection angles θ varying from 7 • to 9.5 • . Mean fields have been obtained in the same facility in previous works (Deleuze & Elena 1996;Laurent 1996). Here, we will focus on the unsteadiness related to the shock movements and inside the recirculating flow.…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Space and time organization in a shock-induced separated boundary layer

Dupont¹,

Haddad²,

Debiève³

2006

J. Fluid Mech.

374

229

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The interaction of an oblique shock wave impinging on a turbulent boundary layer at Mach number 2.3 is experimentally investigated for a wide range of shock intensities. Characteristic time and length scales of the unsteady reflected shock and inside the downstream interaction region are obtained and compared with already existing results obtained in compression ramp experiments as well as in subsonic detached flows. Dimensionless characteristic frequencies are highlighted to characterize low-frequency shock unsteadiness as well as the different large scales which develop inside the initial part of the interaction. The possibility of describing the spatial development of the large scales inside the interaction zone using a mixing-layer scheme including compressibility effects is tested for a wide range of Mach numbers, shock intensities and geometrical configurations. Moreover, strong evidence of a statistical link between low-frequency shock movements and the downstream interaction is given. Finally, the downstream evolution of the structures shed into the boundary layer is characterized and shows features specific of our configuration.

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Section: Organization Of the Interactionmentioning

confidence: 95%

Section: Introductionmentioning

confidence: 91%

Section: Incoming Conditions: the Upstream Boundary Layermentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Space and time organization in a shock-induced separated boundary layer

Dupont¹,

Haddad²,

Debiève³

2006

J. Fluid Mech.

374

229

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Investigation by Particle Image Velocimetry Measurements of Oblique Shock Reflection with Separation

et al. 2008

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International audienceThe organization and length scales of turbulent structures and unsteadiness generated in a shock-wave-induced separation at Mach number of 2.3 are investigated experimentally using particle image velocimetry. Processing of the velocity fields displays and demonstrates the existence of structures in the mixing layer developed in the separation bubble. Moreover, we show in evidence a link between the reflected shock excursions and the size of the separated flow. This overview of the spatial organization of the interaction provides a more comprehensive picture of the flow. Nomenclature C f = friction coefficient L = length of the interaction M = Mach number Re = Reynolds number based on the momentum thickness S L = Strouhal number T t = stagnation temperature U 0 = upstream external velocity U = V=u u = friction velocity V = Van Driest transformed velocity X = x X 0 =L X 0 = mean position of the reflected shock x = longitudinal coordinate Y = y= 0 y = normal to the wall coordinate y = yu = 0 = upstream boundary-layer thickness = incidence angle of the shock generator = kinematic viscosit

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RTO WG 10 - Test cases for CFD validation of hypersonic flight

Knight¹

2002

40th AIAA Aerospace Sciences Meeting &Amp; Exhibit

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Some Turbulence Characteristics Downstream a Shock Wave - Boundary Layer Interaction

Cited by 3 publications

References 1 publication

Space and time organization in a shock-induced separated boundary layer

Space and time organization in a shock-induced separated boundary layer

Investigation by Particle Image Velocimetry Measurements of Oblique Shock Reflection with Separation

RTO WG 10 - Test cases for CFD validation of hypersonic flight

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