Experimental study on the PRE-X vehicle focusing on the transitional shock-wave/boundary-layer interactions

Bur, Reynald; Chanetz, Bruno

doi:10.1016/j.ast.2009.09.002

Cited by 25 publications

(10 citation statements)

References 5 publications

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“…Convective instabilities were found to be largest for oblique first modes (in agreement with the study of Yao et al 2007 cited above). A continuation of this work was published by Bur & Chanetz (2009). This study noted that heat transfer can be higher in transitional interactions.…”

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confidence: 58%

Transitional shock-wave/boundary-layer interactions in hypersonic flow

et al. 2014

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Strong interactions of shock waves with boundary layers lead to flow separations and enhanced heat transfer rates. When the approaching boundary layer is hypersonic and transitional the problem is particularly challenging and more reliable data is required in order to assess changes in the flow and the surface heat transfer, and to develop simplified models. The present contribution compares results for transitional interactions on a flat plate at Mach 6 from three different experimental facilities using the same instrumented plate insert. The facilities consist of a Ludwieg tube (RWG), an open-jet wind tunnel (H2K) and a high-enthalpy free-piston-driven reflected shock tunnel (HEG). The experimental measurements include shadowgraph and infrared thermography as well as heat transfer and pressure sensors. Direct numerical simulations (DNS) are carried out to compare with selected experimental flow conditions. The combined approach allows an assessment of the effects of unit Reynolds number, disturbance amplitude, shock impingement location and wall cooling. Measures of intermittency are proposed based on wall heat flux, allowing the peak Stanton number in the reattachment regime to be mapped over a range of intermittency states of the approaching boundary layer, with higher overshoots found for transitional interactions compared with fully turbulent interactions. The transition process is found to develop from second (Mack) mode instabilities superimposed on streamwise streaks.

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confidence: 58%

Transitional shock-wave/boundary-layer interactions in hypersonic flow

et al. 2014

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“…The temperature of the wall is imposed at 290 K to reproduce the experimental conditions of Benay et al. (2006) and Bur & Chanetz (2009). Standard supersonic inflow, outflow and far field conditions are used for the other boundaries.…”

Section: Numerical Simulationsmentioning

confidence: 99%

“…However, taking into account the transitional process is essential when designing hypersonic vehicles. Bur & Chanetz (2009) studied the impact of transition through a SBLI on the European pre-X demonstrator and showed how crucial it is to get a better understanding of the transitional process for this type of flow. For instance, the wall heat-flux peak, another main limiting factor of hypersonic flight, could be more than 20 to 30 % higher than the turbulent one in the transition region.…”

Section: Introductionmentioning

confidence: 99%

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Transition scenario in hypersonic axisymmetrical compression ramp flow

et al. 2020

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“…While some studies cited here-before bring interesting information about the new instabilities and amplification mechanisms originating from the SBLI and the separated region, they mainly focus on one single type of instability or amplification mechanism and postulate that it may be responsible for transition to turbulence. Though, Bur et al [25] experimentally studied the impact of transition through a SBLI on the European Pre-X demonstrator and showed that it is crucial to understand the transition process better when dealing with control surface separation in real-life designs. In this context, a study combining the multiple known mechanisms up to the actual transition is still lacking from the literature.…”

Section: Introductionmentioning

confidence: 99%

Multi-scale study of the transitional shock-wave boundary layer interaction in hypersonic flow

Lugrin

Beneddine

Garnier

et al. 2021

Theor. Comput. Fluid Dyn.

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A high-fidelity simulation of the massively separated shock/ transitional boundary layer interaction caused by a 15-degrees axisymmetrical compression ramp is performed at a free stream Mach number of 6 and a transitional Reynolds number. The chosen configuration yields a strongly multiscale dynamics of the flow as the separated region oscillates at low-frequency, and high-frequency transitional instabilities are triggered by the injection of a generic noise at the inlet of the simulation. The simulation is post-processed using Proper Orthogonal Decomposition to extract the large scale low-frequency dynamics of the recirculation region. The bubble dynamics from the simulation is then compared to the results of a global linear stability analysis about the mean flow. A critical interpretation of the eigenspectrum of the linearized Navier-Stokes operator is presented. The recirculation region dynamics is found to be dominated by two coexisting modes, a quasi-steady one that expresses itself mainly in the reattachment region and that is caused by the interaction of two self-sustained instabilities, and an unsteady one linked with the separation shock-wave and the mixing layer. The unsteady mode is driven by a feedback loop in the recirculation region, which may also be relevant for other unsteady shock-motion already documented for shock-wave/turbulent boundary layer interaction. The impact of the large-scale dynamics on the transitional one is then assessed through the numerical filtering of those low wavenumber modes; they are found to have no impact on the transitional dynamics.

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Experimental study on the PRE-X vehicle focusing on the transitional shock-wave/boundary-layer interactions

Cited by 25 publications

References 5 publications

Transitional shock-wave/boundary-layer interactions in hypersonic flow

Transitional shock-wave/boundary-layer interactions in hypersonic flow

Transition scenario in hypersonic axisymmetrical compression ramp flow

Multi-scale study of the transitional shock-wave boundary layer interaction in hypersonic flow

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