On the behavior of upwind schemes applied to three-dimensional supersonic and hypersonic cold gas flow simulations of aerospace configurations.
Ano de defesa: | 2007 |
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Autor(a) principal: | |
Orientador(a): | |
Banca de defesa: | |
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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Biblioteca Digital de Teses e Dissertações do ITA |
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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 |
_version_ |
1706804987260043264 |