An unstructured grid approach to the solution of axisymmetric launch vehicle flows.
Ano de defesa: | 2001 |
---|---|
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=2444 |
Resumo: | A study of the flowfield around axisymmetric launch vehicles in different flight conditions and configurations is performed in this work. Particularly, the VLS second stage flight configuration is analyzed considering the case with and without a propulsive jet in the vehicle base. Among the different cases considered for this configuration there are inviscid as well as viscous turbulent flows. The study is performed using a finite volume cell centered formulation on unstructured grids. Different spatial discretization schemes are compared, including a centered and an upwind scheme. The upwind scheme is a second-order version of the Liou flux vector splitting scheme and a simple scalar advection test problem is used to assess the influence of different reconstruction and limiting methods in the second-order extension of the scheme. Turbulence effects are accounted for using two one-equation turbulence closure models, namely the Baldwin and Barth and the Spalart and Allmaras models. An agglomeration multigrid algorithm is used to accelerate the convergence to steady state of the numerical solutions. Mesh refinement procedures as well as hybrid and adaptive meshes are discussed. |
id |
ITA_0f2d1c41b8d13b0d15d9a644b2bf34e9 |
---|---|
oai_identifier_str |
oai:agregador.ibict.br.BDTD_ITA:oai:ita.br:2444 |
network_acronym_str |
ITA |
network_name_str |
Biblioteca Digital de Teses e Dissertações do ITA |
spelling |
An unstructured grid approach to the solution of axisymmetric launch vehicle flows.Escoamento turbulentoMétodos de multigridVeículos de lançamentoAnálise numéricaConfigurações aerodinâmicasDinâmica dos fluidos computacionalMecânica dos fluidosAerodinâmicaEngenharia aeronáuticaEngenharia mecânicaA study of the flowfield around axisymmetric launch vehicles in different flight conditions and configurations is performed in this work. Particularly, the VLS second stage flight configuration is analyzed considering the case with and without a propulsive jet in the vehicle base. Among the different cases considered for this configuration there are inviscid as well as viscous turbulent flows. The study is performed using a finite volume cell centered formulation on unstructured grids. Different spatial discretization schemes are compared, including a centered and an upwind scheme. The upwind scheme is a second-order version of the Liou flux vector splitting scheme and a simple scalar advection test problem is used to assess the influence of different reconstruction and limiting methods in the second-order extension of the scheme. Turbulence effects are accounted for using two one-equation turbulence closure models, namely the Baldwin and Barth and the Spalart and Allmaras models. An agglomeration multigrid algorithm is used to accelerate the convergence to steady state of the numerical solutions. Mesh refinement procedures as well as hybrid and adaptive meshes are discussed. Instituto Tecnológico de AeronáuticaJoão Luiz Filgueiras de AzevedoDaniel Strauss2001-00-00info:eu-repo/semantics/publishedVersioninfo:eu-repo/semantics/masterThesishttp://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=2444reponame:Biblioteca Digital de Teses e Dissertações do ITAinstname:Instituto Tecnológico de Aeronáuticainstacron:ITAenginfo:eu-repo/semantics/openAccessapplication/pdf2019-02-02T14:04:48Zoai:agregador.ibict.br.BDTD_ITA:oai:ita.br:2444http://oai.bdtd.ibict.br/requestopendoar:null2020-05-28 19:39:07.351Biblioteca Digital de Teses e Dissertações do ITA - Instituto Tecnológico de Aeronáuticatrue |
dc.title.none.fl_str_mv |
An unstructured grid approach to the solution of axisymmetric launch vehicle flows. |
title |
An unstructured grid approach to the solution of axisymmetric launch vehicle flows. |
spellingShingle |
An unstructured grid approach to the solution of axisymmetric launch vehicle flows. Daniel Strauss Escoamento turbulento Métodos de multigrid Veículos de lançamento Análise numérica Configurações aerodinâmicas Dinâmica dos fluidos computacional Mecânica dos fluidos Aerodinâmica Engenharia aeronáutica Engenharia mecânica |
title_short |
An unstructured grid approach to the solution of axisymmetric launch vehicle flows. |
title_full |
An unstructured grid approach to the solution of axisymmetric launch vehicle flows. |
title_fullStr |
An unstructured grid approach to the solution of axisymmetric launch vehicle flows. |
title_full_unstemmed |
An unstructured grid approach to the solution of axisymmetric launch vehicle flows. |
title_sort |
An unstructured grid approach to the solution of axisymmetric launch vehicle flows. |
author |
Daniel Strauss |
author_facet |
Daniel Strauss |
author_role |
author |
dc.contributor.none.fl_str_mv |
João Luiz Filgueiras de Azevedo |
dc.contributor.author.fl_str_mv |
Daniel Strauss |
dc.subject.por.fl_str_mv |
Escoamento turbulento Métodos de multigrid Veículos de lançamento Análise numérica Configurações aerodinâmicas Dinâmica dos fluidos computacional Mecânica dos fluidos Aerodinâmica Engenharia aeronáutica Engenharia mecânica |
topic |
Escoamento turbulento Métodos de multigrid Veículos de lançamento Análise numérica Configurações aerodinâmicas Dinâmica dos fluidos computacional Mecânica dos fluidos Aerodinâmica Engenharia aeronáutica Engenharia mecânica |
dc.description.none.fl_txt_mv |
A study of the flowfield around axisymmetric launch vehicles in different flight conditions and configurations is performed in this work. Particularly, the VLS second stage flight configuration is analyzed considering the case with and without a propulsive jet in the vehicle base. Among the different cases considered for this configuration there are inviscid as well as viscous turbulent flows. The study is performed using a finite volume cell centered formulation on unstructured grids. Different spatial discretization schemes are compared, including a centered and an upwind scheme. The upwind scheme is a second-order version of the Liou flux vector splitting scheme and a simple scalar advection test problem is used to assess the influence of different reconstruction and limiting methods in the second-order extension of the scheme. Turbulence effects are accounted for using two one-equation turbulence closure models, namely the Baldwin and Barth and the Spalart and Allmaras models. An agglomeration multigrid algorithm is used to accelerate the convergence to steady state of the numerical solutions. Mesh refinement procedures as well as hybrid and adaptive meshes are discussed. |
description |
A study of the flowfield around axisymmetric launch vehicles in different flight conditions and configurations is performed in this work. Particularly, the VLS second stage flight configuration is analyzed considering the case with and without a propulsive jet in the vehicle base. Among the different cases considered for this configuration there are inviscid as well as viscous turbulent flows. The study is performed using a finite volume cell centered formulation on unstructured grids. Different spatial discretization schemes are compared, including a centered and an upwind scheme. The upwind scheme is a second-order version of the Liou flux vector splitting scheme and a simple scalar advection test problem is used to assess the influence of different reconstruction and limiting methods in the second-order extension of the scheme. Turbulence effects are accounted for using two one-equation turbulence closure models, namely the Baldwin and Barth and the Spalart and Allmaras models. An agglomeration multigrid algorithm is used to accelerate the convergence to steady state of the numerical solutions. Mesh refinement procedures as well as hybrid and adaptive meshes are discussed. |
publishDate |
2001 |
dc.date.none.fl_str_mv |
2001-00-00 |
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=2444 |
url |
http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=2444 |
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 |
Escoamento turbulento Métodos de multigrid Veículos de lançamento Análise numérica Configurações aerodinâmicas Dinâmica dos fluidos computacional Mecânica dos fluidos Aerodinâmica Engenharia aeronáutica Engenharia mecânica |
_version_ |
1706804999962492928 |