Advanced turbulence modelling for complex aerospace applications.

Detalhes bibliográficos
Autor(a) principal: Enda Dimitri Vieira Bigarella
Data de Publicação: 2007
Tipo de documento: Tese
Idioma: eng
Título da fonte: Biblioteca Digital de Teses e Dissertações do ITA
Texto Completo: http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=418
Resumo: The objective of the present research work consists in studying complex aerodynamic flows about typical aerospace configuration, in which turbulence effects play a fundamental role. Such study is performed with an available computational tool that is being developed at CTA/IAE. This is a finite-volume code for unstructured 3-D meshes that solves the compressible Reynolds-averaged Navier-Stokes equations. Turbulence effects are added to this numerical tool through turbulence models. Similar work had already been initiated by the author in his master thesis at ITA with less advanced model in that context. Turbulence effects are critical for complex aerospace configurations, such as supercritical or high-lift aerofoils, or space vehicles at atmospheric transonic or supersonic flight, and less advanced turbulence models fail to adequately describe such flows. The investment in more complex turbulence models, such as {em nonlinear} eddy viscosity and Reynolds-stress transport closures, is of fundamental importance to better capture such flows, which are very important in the context of the developments within the aerospace area at CTA/IAE and Embraer. Furthermore, in order to allow for a robust and efficient numerical framework, effort is also driven towards convergence acceleration techniques such as multigrid and variable time stepping procedures, as well as convective flux computation schemes suitable for boundary layer and shocked flows. These flux schemes must be robust and accurate even for highly stretched meshes that support these flow phenomena at reasonable computational costs. The validation of these new implementations, for the applications of interest, is performed by comparison of numerical results with experimental or theoretical data for several flow cases. Flows involving laminar boundary layers and shock waves are used to assess the quality of the convective flux computation schemes. Traditional turbulent-flow validation cases, such as the turbulent boundary layers over a flat plate or within a parallel-wall channel, are considered to address the level of physical representativeness of the chosen models. Finally, typical aerospace flows are evaluated with the best numerical settings resulting from the previously mentioned efforts. Such cases involve transonic and high-lift aerofoils, and transonic and supersonic flows about a space vehicle. In general, good agreement of numerical results with the reference data is obtained.
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spelling Advanced turbulence modelling for complex aerospace applications.Dinâmica dos fluidos computacionalEscoamento turbulentoConfigurações aerodinâmicasModelos matemáticosCódigos computacionaisCamada limite laminarOndas de choqueMecânica dos fluidosFísicaEngenharia aeronáuticaThe objective of the present research work consists in studying complex aerodynamic flows about typical aerospace configuration, in which turbulence effects play a fundamental role. Such study is performed with an available computational tool that is being developed at CTA/IAE. This is a finite-volume code for unstructured 3-D meshes that solves the compressible Reynolds-averaged Navier-Stokes equations. Turbulence effects are added to this numerical tool through turbulence models. Similar work had already been initiated by the author in his master thesis at ITA with less advanced model in that context. Turbulence effects are critical for complex aerospace configurations, such as supercritical or high-lift aerofoils, or space vehicles at atmospheric transonic or supersonic flight, and less advanced turbulence models fail to adequately describe such flows. The investment in more complex turbulence models, such as {em nonlinear} eddy viscosity and Reynolds-stress transport closures, is of fundamental importance to better capture such flows, which are very important in the context of the developments within the aerospace area at CTA/IAE and Embraer. Furthermore, in order to allow for a robust and efficient numerical framework, effort is also driven towards convergence acceleration techniques such as multigrid and variable time stepping procedures, as well as convective flux computation schemes suitable for boundary layer and shocked flows. These flux schemes must be robust and accurate even for highly stretched meshes that support these flow phenomena at reasonable computational costs. The validation of these new implementations, for the applications of interest, is performed by comparison of numerical results with experimental or theoretical data for several flow cases. Flows involving laminar boundary layers and shock waves are used to assess the quality of the convective flux computation schemes. Traditional turbulent-flow validation cases, such as the turbulent boundary layers over a flat plate or within a parallel-wall channel, are considered to address the level of physical representativeness of the chosen models. Finally, typical aerospace flows are evaluated with the best numerical settings resulting from the previously mentioned efforts. Such cases involve transonic and high-lift aerofoils, and transonic and supersonic flows about a space vehicle. In general, good agreement of numerical results with the reference data is obtained.Instituto Tecnológico de AeronáuticaJoão Luiz Filgueiras de AzevedoEnda Dimitri Vieira Bigarella2007-10-11info:eu-repo/semantics/publishedVersioninfo:eu-repo/semantics/doctoralThesishttp://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=418reponame: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:418http://oai.bdtd.ibict.br/requestopendoar:null2020-05-28 19:33:13.478Biblioteca Digital de Teses e Dissertações do ITA - Instituto Tecnológico de Aeronáuticatrue
dc.title.none.fl_str_mv Advanced turbulence modelling for complex aerospace applications.
title Advanced turbulence modelling for complex aerospace applications.
spellingShingle Advanced turbulence modelling for complex aerospace applications.
Enda Dimitri Vieira Bigarella
Dinâmica dos fluidos computacional
Escoamento turbulento
Configurações aerodinâmicas
Modelos matemáticos
Códigos computacionais
Camada limite laminar
Ondas de choque
Mecânica dos fluidos
Física
Engenharia aeronáutica
title_short Advanced turbulence modelling for complex aerospace applications.
title_full Advanced turbulence modelling for complex aerospace applications.
title_fullStr Advanced turbulence modelling for complex aerospace applications.
title_full_unstemmed Advanced turbulence modelling for complex aerospace applications.
title_sort Advanced turbulence modelling for complex aerospace applications.
author Enda Dimitri Vieira Bigarella
author_facet Enda Dimitri Vieira Bigarella
author_role author
dc.contributor.none.fl_str_mv João Luiz Filgueiras de Azevedo
dc.contributor.author.fl_str_mv Enda Dimitri Vieira Bigarella
dc.subject.por.fl_str_mv Dinâmica dos fluidos computacional
Escoamento turbulento
Configurações aerodinâmicas
Modelos matemáticos
Códigos computacionais
Camada limite laminar
Ondas de choque
Mecânica dos fluidos
Física
Engenharia aeronáutica
topic Dinâmica dos fluidos computacional
Escoamento turbulento
Configurações aerodinâmicas
Modelos matemáticos
Códigos computacionais
Camada limite laminar
Ondas de choque
Mecânica dos fluidos
Física
Engenharia aeronáutica
dc.description.none.fl_txt_mv The objective of the present research work consists in studying complex aerodynamic flows about typical aerospace configuration, in which turbulence effects play a fundamental role. Such study is performed with an available computational tool that is being developed at CTA/IAE. This is a finite-volume code for unstructured 3-D meshes that solves the compressible Reynolds-averaged Navier-Stokes equations. Turbulence effects are added to this numerical tool through turbulence models. Similar work had already been initiated by the author in his master thesis at ITA with less advanced model in that context. Turbulence effects are critical for complex aerospace configurations, such as supercritical or high-lift aerofoils, or space vehicles at atmospheric transonic or supersonic flight, and less advanced turbulence models fail to adequately describe such flows. The investment in more complex turbulence models, such as {em nonlinear} eddy viscosity and Reynolds-stress transport closures, is of fundamental importance to better capture such flows, which are very important in the context of the developments within the aerospace area at CTA/IAE and Embraer. Furthermore, in order to allow for a robust and efficient numerical framework, effort is also driven towards convergence acceleration techniques such as multigrid and variable time stepping procedures, as well as convective flux computation schemes suitable for boundary layer and shocked flows. These flux schemes must be robust and accurate even for highly stretched meshes that support these flow phenomena at reasonable computational costs. The validation of these new implementations, for the applications of interest, is performed by comparison of numerical results with experimental or theoretical data for several flow cases. Flows involving laminar boundary layers and shock waves are used to assess the quality of the convective flux computation schemes. Traditional turbulent-flow validation cases, such as the turbulent boundary layers over a flat plate or within a parallel-wall channel, are considered to address the level of physical representativeness of the chosen models. Finally, typical aerospace flows are evaluated with the best numerical settings resulting from the previously mentioned efforts. Such cases involve transonic and high-lift aerofoils, and transonic and supersonic flows about a space vehicle. In general, good agreement of numerical results with the reference data is obtained.
description The objective of the present research work consists in studying complex aerodynamic flows about typical aerospace configuration, in which turbulence effects play a fundamental role. Such study is performed with an available computational tool that is being developed at CTA/IAE. This is a finite-volume code for unstructured 3-D meshes that solves the compressible Reynolds-averaged Navier-Stokes equations. Turbulence effects are added to this numerical tool through turbulence models. Similar work had already been initiated by the author in his master thesis at ITA with less advanced model in that context. Turbulence effects are critical for complex aerospace configurations, such as supercritical or high-lift aerofoils, or space vehicles at atmospheric transonic or supersonic flight, and less advanced turbulence models fail to adequately describe such flows. The investment in more complex turbulence models, such as {em nonlinear} eddy viscosity and Reynolds-stress transport closures, is of fundamental importance to better capture such flows, which are very important in the context of the developments within the aerospace area at CTA/IAE and Embraer. Furthermore, in order to allow for a robust and efficient numerical framework, effort is also driven towards convergence acceleration techniques such as multigrid and variable time stepping procedures, as well as convective flux computation schemes suitable for boundary layer and shocked flows. These flux schemes must be robust and accurate even for highly stretched meshes that support these flow phenomena at reasonable computational costs. The validation of these new implementations, for the applications of interest, is performed by comparison of numerical results with experimental or theoretical data for several flow cases. Flows involving laminar boundary layers and shock waves are used to assess the quality of the convective flux computation schemes. Traditional turbulent-flow validation cases, such as the turbulent boundary layers over a flat plate or within a parallel-wall channel, are considered to address the level of physical representativeness of the chosen models. Finally, typical aerospace flows are evaluated with the best numerical settings resulting from the previously mentioned efforts. Such cases involve transonic and high-lift aerofoils, and transonic and supersonic flows about a space vehicle. In general, good agreement of numerical results with the reference data is obtained.
publishDate 2007
dc.date.none.fl_str_mv 2007-10-11
dc.type.driver.fl_str_mv info:eu-repo/semantics/publishedVersion
info:eu-repo/semantics/doctoralThesis
status_str publishedVersion
format doctoralThesis
dc.identifier.uri.fl_str_mv http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=418
url http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=418
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 fluidos computacional
Escoamento turbulento
Configurações aerodinâmicas
Modelos matemáticos
Códigos computacionais
Camada limite laminar
Ondas de choque
Mecânica dos fluidos
Física
Engenharia aeronáutica
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