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Strong scaling of numerical solver for supersonic jet flow configurations

Article dans une revue avec comité de lecture
Author
JUNQUEIRA-JUNIOR, Carlos
134975 Laboratoire de Dynamique des Fluides [DynFluid]
AZEVEDO, João Luiz F.
471029 Instituto Tecnológico de Aeronáutica [São José dos Campos] [ITA]
PANETTA, Jairo
WOLF, William R.
YAMOUNI, Sami

URI
http://hdl.handle.net/10985/17676
DOI
10.1007/s40430-019-2055-6
Date
2019
Journal
Journal of the Brazilian Society of Mechanical Sciences and Engineering

Abstract

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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