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(Referência obtida automaticamente do Web of Science, por meio da informação sobre o financiamento pela FAPESP e o número do processo correspondente, incluída na publicação pelos autores.)

Numerical simulations of three-dimensional flow over a multi-stage rocket using finite volumes

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Autor(es):
Scalabrin, Leonardo Costa [1] ; Azevedo, Joao Luiz F. [2]
Número total de Autores: 2
Afiliação do(s) autor(es):
[1] Embraer SA, BR-12227901 Sao Jose Dos Campos, SP - Brazil
[2] DCTA IAE ALA, Dept Ciencia & Tecnol Aeroespacial, Inst Aeronaut & Espaco, BR-12228903 Sao Jose Dos Campos, SP - Brazil
Número total de Afiliações: 2
Tipo de documento: Artigo Científico
Fonte: Journal of the Brazilian Society of Mechanical Sciences and Engineering; v. 38, n. 1, p. 1-20, JAN 2016.
Citações Web of Science: 0
Resumo

The paper discusses the results obtained using an in-house developed finite volume code for three-dimensional, unstructured, adaptive meshes to simulate inviscid and viscous flows. A fully explicit, second-order accurate, five-stage, Runge-Kutta time-stepping scheme is used to perform the time march of the flow equations. Two different forms for flux calculation on the volume faces are implemented. The first one is a centered scheme which requires the addition of artificial dissipation terms. The other form for flux calculation is based on the van Leer flux-vector splitting scheme. The boundary conditions are set using Riemann invariants. The implementation uses a cell-centered, face-based data structure. The Spalart and Allmaras turbulence model is implemented to simulate viscous flows at high Reynolds numbers. In order to enhance the quality of the results, h-refinement routines are implemented in the code to adapt the original mesh. These routines are able to handle tetrahedra, hexahedra, triangular base prisms and quadrilateral base pyramids. A sensor based on density gradients selects the elements to be refined. The paper presents simulation results obtained for the Brazilian Satellite Launcher. The simulations using the adaptive mesh refinement routines are performed for inviscid flows. The paper also presents simulations of transonic and supersonic turbulent viscous flows over the vehicle. (AU)

Processo FAPESP: 04/16064-9 - Mecânica dos fluídos não estacionária: aplicações em aeronáutica e em reologia
Beneficiário:José Alberto Cuminato
Linha de fomento: Auxílio à Pesquisa - Temático
Processo FAPESP: 11/12493-6 - Investigação de geração e propagação de ruído próprio de aerofólios usando simulação de grandes escalas, modelos analíticos e analogia acústica
Beneficiário:William Roberto Wolf
Linha de fomento: Bolsas no Brasil - Pós-Doutorado