Wall-Modeled Large-Eddy Simulations of Shock/Turbulent-Boundary-Layer Interactions in a Low Aspect-Ratio Duct

Bermejo-Moreno, Iván; Campo, Laura; Larsson, Johan; Bodart, Julien; Helmer, David; Eaton, John K.

doi:10.1615/tsfp8.570

Cited by 3 publications

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“…Additionally, the simulations of the ONERA/JAXA configuration by Fureby et al (2015) quantified the effects of alternating-wedge injection struts on mixing and combustion characteristics. The HIFiRE-2 simulations by Bermejo-Moreno et al (2013) innovatively employed low-dissipation numerics along with an equilibrium wall model to treat near-wall turbulence in the boundary layers (Figure 11) and revealed large-scale oscillations of the shock train in the engine core that may have influences on the development of combustion dynamics. The HiFIRE-2 scramjet has also been computationally addressed by Saghafian et al (2015a), who showed that the equilibrium wall model, in conjunction with the flamelet compressibility corrections for pressure and temperature described in Section 3.2.1, leads to improved agreement with the experiments of Cabell et al (2011).…”

Section: Turbulent Supersonic Combustion Modelingmentioning

confidence: 99%

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Supersonic Combustion in Air-Breathing Propulsion Systems for Hypersonic Flight

Urzay

2018

Annu. Rev. Fluid Mech.

366

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Great efforts have been dedicated during the last decades to the research and development of hypersonic aircrafts that can fly at several times the speed of sound. These aerospace vehicles have revolutionary applications in national security as advanced hypersonic weapons, in space exploration as reusable stages for access to low Earth orbit, and in commercial aviation as fast long-range methods for air transportation of passengers around the globe. This review addresses the topic of supersonic combustion, which represents the central physical process that enables scramjet hypersonic propulsion systems to accelerate aircrafts to ultra-high speeds. The description focuses on recent experimental flights and ground-based research programs and highlights associated fundamental flow physics, subgrid-scale model development, and full-system numerical simulations.

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Section: Turbulent Supersonic Combustion Modelingmentioning

confidence: 99%

“…Figure 11Wall-modeled large-eddy simulation of the HIFiRE-2 scramjet (see configuration schematics in Figure5a) showing instantaneous isocontours of temperature, density gradient, pressure, and wall-parallel velocity at the exchange location with the wall model. Adapted with permission fromBermejo-Moreno et al (2013).…”

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confidence: 99%