2021
DOI: 10.1016/j.camwa.2019.10.017
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Large eddy simulation of pseudo shock structure in a convergent–long divergent duct

Abstract: In this paper, the Pseudo shock structure in a convergent-long divergent duct is investigated using large eddy simulation on the basis of Smagorinsky-Lilly, Wall-Adapting Local Eddy-Viscosity and Algebraic Wall-Modeled LES subgrid models. The first objective of the study is to apply different subgrid models to predict the structure of Lambda form shocks system, while the ultimate aim is to obtain further control of the shock behavior. To achieve these goals, the dynamic grid adaption and hybrid initialization … Show more

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Cited by 26 publications
(4 citation statements)
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References 55 publications
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“…WMLES uses the Reynolds average method to simulate the flow field in the inner region of the boundary layer, and uses a LES method to simulate outside the near-wall region [24][25][26] C is a constant.…”
Section: Construction Of Sub-lattice Modelmentioning
confidence: 99%
“…WMLES uses the Reynolds average method to simulate the flow field in the inner region of the boundary layer, and uses a LES method to simulate outside the near-wall region [24][25][26] C is a constant.…”
Section: Construction Of Sub-lattice Modelmentioning
confidence: 99%
“…However, because the liquid in the boiler pipeline experiences a high-pressure environment, the flow also makes the corrosion process more intense. Numerous studies have shown that the rapid fluid has an adverse effect on the deposition of products at the interface and the presence of bumps around the weld leads to the formation of local turbulence when the liquid flows through [ 14 , 15 , 16 ]. It not only enhances the erosion and corrosion of the pipeline [ 17 , 18 ], but also further alters the microscopic morphology of the interface owing to the change of the corrosion scale.…”
Section: Introductionmentioning
confidence: 99%
“…The hypersonic inlet, as the intake device of a scramjet engine, is involved in capturing sufficient air and compressing it effectively so as to provide air at the required mass flow rate, pressure ratio, temperature, and speed for the combustor, allowing the engine to generate enough thrust to achieve hypersonic flight (Chang et al, 2017). The flow field quality and reliable operation of the hypersonic inlet directly determine the performance and working range of the engine and are related to the flight speed of an aircraft (Devaraj et al, 2020, Kamali et al, 2016a, Li et al 2022, Mousavi et al, 2018a, Rad and Mousavi, 2015a, Sotoudeh et al, 2019b, Sun et al, 2019, Wang et al, 2019a, 2016). Shock wave/boundary layer interactions occur in the inlet when a shock wave and a boundary layer converge and, since both can be found in almost every supersonic flow, these interactions are commonplace (Kamali et al, 2015, Mousavi and Roohi, 2014b, Rad and Mousavi, 2015b, Sotoudeh et al, 2019b).…”
Section: Introductionmentioning
confidence: 99%
“…Shock wave/boundary layer interactions can lead to deterioration of flow field quality and bring aerodynamic/ thermal loads and pressure fluctuations to wall surface, which can easily cause surface structure failure and inlet unstart Roohi, 2014a, Kamali et al, 2016b). It is one of the key aerodynamic challenges faced in the development of hypersonic inlet and must be handled carefully (Mousavi et al, 2018b(Mousavi et al, , 2021.…”
Section: Introductionmentioning
confidence: 99%