Influence of different subgrid-scale models in low-order LES of supersonic jet flows

Junqueira-Junior, Carlos; Yamouni, Sami; Azevedo, João Luiz F.; Wolf, William

doi:10.1007/s40430-018-1182-9

Cited by 6 publications

(10 citation statements)

References 27 publications

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“…Isothermal and zerovelocity conditions, along with a zero-pressure-gradient state, consistent with the freestream condition, are used as initial conditions for the simulations. The JAZzY solver has already been validated and presented good results using such flow configuration [11]. The reader can find more details about this flow configuration in the Compressible Jet Flow Simulation section.…”

Section: Scalability Setupmentioning

confidence: 99%

“…Therefore, the authors have devel-oped a numerical tool, JAZzY [5], based on the large eddy simulation (LES) formulation [6] in order to perform timedependent simulations of supersonic compressible jet flows. The large eddy simulation approach has been successfully used by the scientific community and can provide high fidelity numerical data for aeroacoustic applications [7,8,9,10,11]. The numerical tool is written in the Fortran 90 standards coupled with Message Passing Interface (MPI) features [12].…”

Section: Introductionmentioning

confidence: 99%

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On the scalability of CFD tool for supersonic jet flow configurations

et al. 2020

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New regulations are imposing noise emissions limitations for the aviation industry which are pushing researchers and engineers to invest efforts in studying the aeroacoustics phenomena. Following this trend, an in-house computational fluid dynamics tool is build to reproduce high fidelity results of supersonic jet flows for aeroacoustic analogy applications. The solver is written using the large eddy simulation formulation that is discretized using a finite difference approach and an explicit time integration. Numerical simulations of supersonic jet flows are very expensive and demand efficient high-performance computing. Therefore, non-blocking message passage interface protocols and parallel Input/Output features are implemented into the code in order to perform simulations which demand up to one billion grid points. The present work addresses the evaluation of code improvements along with the computational performance of the solver running on a computer with maximum theoretical peak of 2.727 PFlops. Different mesh configurations, whose size varies from a few hundred thousand to approximately one billion grid points, are evaluated in the present paper. Calculations are performed using different workloads in order to assess the strong and weak scalability of the parallel computational tool. Moreover, validation results of a realistic flow condition are also presented in the current work.

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Section: Scalability Setupmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

On the scalability of CFD tool for supersonic jet flow configurations

et al. 2020

Self Cite

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show abstract

“…In the present article, the eddy viscosity coefficient, µsgs, and the components of the isotropic part of the SGS stress tensor, σ kk , are not considered for the calculations. Previous validation results performed by the authors [17,18] indicate that the characteristics of numerical discretization of JAZzY can overcome the effects of subgrid scale models. The same conclusion can be found in the work of Li and Wang [20].…”

Section: Computational Resourcesmentioning

confidence: 99%

“…JAZzY is a compressible LES parallel code for the calculation of supersonic jet flow configurations. The large eddy simulation approach has been successfully used by the scientific community and can provide high fidelity numerical data for aeroacoustic applications [3,36,21,37,18]. The numerical tool is written in the Fortran 90 standards coupled with Message Passing Interface (MPI) features [8].…”

Section: Introductionmentioning

confidence: 99%

“…Large eddy simulations require a significant amount of computational resources to provide high fidelity results. The scientific community has been using up to hundreds of million degrees of freedom on simulations of turbulent flow configurations [6,12,18,32]. Researchers and engineers need to be certain that calculations are run with maximum parallel efficiency when allocating computational resources because the access to supercomputers is often restricted and limited.…”

Section: Introductionmentioning

confidence: 99%

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Strong scaling of numerical solver for supersonic jet flow configurations

Junqueira-Junior

Azevedo

Panetta

et al. 2019

J Braz. Soc. Mech. Sci. Eng.

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Acoustics loads are rocket design constraints which push researches and engineers to invest efforts in the aeroacoustics phenomena which is present on launch vehicles. Therefore, an in-house computational fluid dynamics tool is developed in order to reproduce high fidelity results of supersonic jet flows for aeroacoustic analogy applications. The solver is written using the large eddy simulation formulation that is discretized using a finite difference approach and an explicit time integration. Numerical simulations of supersonic jet flows are very expensive and demand efficient high-performance computing. Therefore, non-blocking message passage interface protocols and parallel Input/Output features are implemented into the code in order to perform simulations which demand up to one billion degrees of freedom. The present work evaluates the parallel efficiency of the solver when running on a supercomputer with a maximum theoretical peak of 127.4 TFLOPS. Speedup curves are generated using nine different workloads. Moreover, the validation results of a realistic flow condition are also presented in the current work.

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Study of the effects of artificial dissipation and other numerical parameters on shock wave resolution

Oliveira,

Azevedo

2023

J Braz. Soc. Mech. Sci. Eng.

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Influence of different subgrid-scale models in low-order LES of supersonic jet flows

Cited by 6 publications

References 27 publications

On the scalability of CFD tool for supersonic jet flow configurations

On the scalability of CFD tool for supersonic jet flow configurations

Strong scaling of numerical solver for supersonic jet flow configurations

Study of the effects of artificial dissipation and other numerical parameters on shock wave resolution

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