On the behavior of upwind schemes applied to three-dimensional supersonic and hypersonic cold gas flow simulations of aerospace configurations.

Detalhes bibliográficos
Ano de defesa: 2007
Autor(a) principal: Farney Coutinho Moreira
Orientador(a): Não Informado pela instituição
Banca de defesa: Não Informado pela instituição
Tipo de documento: Dissertação
Tipo de acesso: Acesso aberto
Idioma: eng
Instituição de defesa: Instituto Tecnológico de Aeronáutica
Programa de Pós-Graduação: Não Informado pela instituição
Departamento: Não Informado pela instituição
País: Não Informado pela instituição
Palavras-chave em Português:
Link de acesso: http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=397
Resumo: The present work describes the efforts towards the implementation of upwind schemes to simulate supersonic and hypersonic cold gás flows. The class of flux vector splitting schemes has been chosen, and the particular methods implemented are the van Leer and Liou schemes. Results for different freestream Mach numbers and mesh topologies are discussed in order to assess the comparative performance of the various spatial discretization schemes. The flow is modeled by 3-D Euler equations through the use of a cell centered, face-based data structure finite voluma method applied in an unstructured grid context. Time integration of the system of equations is performed using an explicit, 5-stage, Runge-Kutta scheme. Mesh refinement routines are available in the original code and they are able to handle tetrahedra, hexahedra, triangular-base prisms and square-base pyramids. The full multigrid procedure is also available in the base code to accelerate the convergence to steady state. In the present work, the author has studied possible forms of integrating the multigrid and the mesh refinement procedures, which were both originally available in the base code. The results obtained provide evaluation and comparison of the present methods with regard to oblique shock wave capturing, as well as the behavior of property values such as pressure, density and Mach number contours. Finally, the work presents a discussion on the relative characteristics of each method.
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spelling On the behavior of upwind schemes applied to three-dimensional supersonic and hypersonic cold gas flow simulations of aerospace configurations.Dinâmica dos gasesEscoamento supersônicoEscoamento hipersônicoCaracterísticas aerodinâmicasMalhas não-estruturadas (Matemática)Método de volume finitoDinâmica dos fluidos computacionalMecânica dos fluidosFísicaThe present work describes the efforts towards the implementation of upwind schemes to simulate supersonic and hypersonic cold gás flows. The class of flux vector splitting schemes has been chosen, and the particular methods implemented are the van Leer and Liou schemes. Results for different freestream Mach numbers and mesh topologies are discussed in order to assess the comparative performance of the various spatial discretization schemes. The flow is modeled by 3-D Euler equations through the use of a cell centered, face-based data structure finite voluma method applied in an unstructured grid context. Time integration of the system of equations is performed using an explicit, 5-stage, Runge-Kutta scheme. Mesh refinement routines are available in the original code and they are able to handle tetrahedra, hexahedra, triangular-base prisms and square-base pyramids. The full multigrid procedure is also available in the base code to accelerate the convergence to steady state. In the present work, the author has studied possible forms of integrating the multigrid and the mesh refinement procedures, which were both originally available in the base code. The results obtained provide evaluation and comparison of the present methods with regard to oblique shock wave capturing, as well as the behavior of property values such as pressure, density and Mach number contours. Finally, the work presents a discussion on the relative characteristics of each method.Instituto Tecnológico de AeronáuticaJoão Luiz Filgueiras de AzevedoFarney Coutinho Moreira2007-07-15info:eu-repo/semantics/publishedVersioninfo:eu-repo/semantics/masterThesishttp://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=397reponame:Biblioteca Digital de Teses e Dissertações do ITAinstname:Instituto Tecnológico de Aeronáuticainstacron:ITAenginfo:eu-repo/semantics/openAccessapplication/pdf2019-02-02T14:01:48Zoai:agregador.ibict.br.BDTD_ITA:oai:ita.br:397http://oai.bdtd.ibict.br/requestopendoar:null2020-05-28 19:33:13.613Biblioteca Digital de Teses e Dissertações do ITA - Instituto Tecnológico de Aeronáuticatrue
dc.title.none.fl_str_mv On the behavior of upwind schemes applied to three-dimensional supersonic and hypersonic cold gas flow simulations of aerospace configurations.
title On the behavior of upwind schemes applied to three-dimensional supersonic and hypersonic cold gas flow simulations of aerospace configurations.
spellingShingle On the behavior of upwind schemes applied to three-dimensional supersonic and hypersonic cold gas flow simulations of aerospace configurations.
Farney Coutinho Moreira
Dinâmica dos gases
Escoamento supersônico
Escoamento hipersônico
Características aerodinâmicas
Malhas não-estruturadas (Matemática)
Método de volume finito
Dinâmica dos fluidos computacional
Mecânica dos fluidos
Física
title_short On the behavior of upwind schemes applied to three-dimensional supersonic and hypersonic cold gas flow simulations of aerospace configurations.
title_full On the behavior of upwind schemes applied to three-dimensional supersonic and hypersonic cold gas flow simulations of aerospace configurations.
title_fullStr On the behavior of upwind schemes applied to three-dimensional supersonic and hypersonic cold gas flow simulations of aerospace configurations.
title_full_unstemmed On the behavior of upwind schemes applied to three-dimensional supersonic and hypersonic cold gas flow simulations of aerospace configurations.
title_sort On the behavior of upwind schemes applied to three-dimensional supersonic and hypersonic cold gas flow simulations of aerospace configurations.
author Farney Coutinho Moreira
author_facet Farney Coutinho Moreira
author_role author
dc.contributor.none.fl_str_mv João Luiz Filgueiras de Azevedo
dc.contributor.author.fl_str_mv Farney Coutinho Moreira
dc.subject.por.fl_str_mv Dinâmica dos gases
Escoamento supersônico
Escoamento hipersônico
Características aerodinâmicas
Malhas não-estruturadas (Matemática)
Método de volume finito
Dinâmica dos fluidos computacional
Mecânica dos fluidos
Física
topic Dinâmica dos gases
Escoamento supersônico
Escoamento hipersônico
Características aerodinâmicas
Malhas não-estruturadas (Matemática)
Método de volume finito
Dinâmica dos fluidos computacional
Mecânica dos fluidos
Física
dc.description.none.fl_txt_mv The present work describes the efforts towards the implementation of upwind schemes to simulate supersonic and hypersonic cold gás flows. The class of flux vector splitting schemes has been chosen, and the particular methods implemented are the van Leer and Liou schemes. Results for different freestream Mach numbers and mesh topologies are discussed in order to assess the comparative performance of the various spatial discretization schemes. The flow is modeled by 3-D Euler equations through the use of a cell centered, face-based data structure finite voluma method applied in an unstructured grid context. Time integration of the system of equations is performed using an explicit, 5-stage, Runge-Kutta scheme. Mesh refinement routines are available in the original code and they are able to handle tetrahedra, hexahedra, triangular-base prisms and square-base pyramids. The full multigrid procedure is also available in the base code to accelerate the convergence to steady state. In the present work, the author has studied possible forms of integrating the multigrid and the mesh refinement procedures, which were both originally available in the base code. The results obtained provide evaluation and comparison of the present methods with regard to oblique shock wave capturing, as well as the behavior of property values such as pressure, density and Mach number contours. Finally, the work presents a discussion on the relative characteristics of each method.
description The present work describes the efforts towards the implementation of upwind schemes to simulate supersonic and hypersonic cold gás flows. The class of flux vector splitting schemes has been chosen, and the particular methods implemented are the van Leer and Liou schemes. Results for different freestream Mach numbers and mesh topologies are discussed in order to assess the comparative performance of the various spatial discretization schemes. The flow is modeled by 3-D Euler equations through the use of a cell centered, face-based data structure finite voluma method applied in an unstructured grid context. Time integration of the system of equations is performed using an explicit, 5-stage, Runge-Kutta scheme. Mesh refinement routines are available in the original code and they are able to handle tetrahedra, hexahedra, triangular-base prisms and square-base pyramids. The full multigrid procedure is also available in the base code to accelerate the convergence to steady state. In the present work, the author has studied possible forms of integrating the multigrid and the mesh refinement procedures, which were both originally available in the base code. The results obtained provide evaluation and comparison of the present methods with regard to oblique shock wave capturing, as well as the behavior of property values such as pressure, density and Mach number contours. Finally, the work presents a discussion on the relative characteristics of each method.
publishDate 2007
dc.date.none.fl_str_mv 2007-07-15
dc.type.driver.fl_str_mv info:eu-repo/semantics/publishedVersion
info:eu-repo/semantics/masterThesis
status_str publishedVersion
format masterThesis
dc.identifier.uri.fl_str_mv http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=397
url http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=397
dc.language.iso.fl_str_mv eng
language eng
dc.rights.driver.fl_str_mv info:eu-repo/semantics/openAccess
eu_rights_str_mv openAccess
dc.format.none.fl_str_mv application/pdf
dc.publisher.none.fl_str_mv Instituto Tecnológico de Aeronáutica
publisher.none.fl_str_mv Instituto Tecnológico de Aeronáutica
dc.source.none.fl_str_mv reponame:Biblioteca Digital de Teses e Dissertações do ITA
instname:Instituto Tecnológico de Aeronáutica
instacron:ITA
reponame_str Biblioteca Digital de Teses e Dissertações do ITA
collection Biblioteca Digital de Teses e Dissertações do ITA
instname_str Instituto Tecnológico de Aeronáutica
instacron_str ITA
institution ITA
repository.name.fl_str_mv Biblioteca Digital de Teses e Dissertações do ITA - Instituto Tecnológico de Aeronáutica
repository.mail.fl_str_mv
subject_por_txtF_mv Dinâmica dos gases
Escoamento supersônico
Escoamento hipersônico
Características aerodinâmicas
Malhas não-estruturadas (Matemática)
Método de volume finito
Dinâmica dos fluidos computacional
Mecânica dos fluidos
Física
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