A study on correction methods for aeroelastic analysis in transonic flow.
Autor(a) principal: | |
---|---|
Data de Publicação: | 2004 |
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=29 |
Resumo: | The work presents a study of correction techniques to compute unsteady transonic pressure distributions and aeroelastic stability in this flow regime. The methodologies herein investigated are based on corrections of pressure distributions by the weighting of the lifting surface self-induced downwash, resulting from aeroelastic structural displacements or prescribed motions. A number approaches were investigated. An investigation into the linear/nonlinear behavior of unsteady transonic flows was also conducted. It was concluded from such investigation that unsteady transonic flows present a linear behavior with respect to small aeroelastic structural displacements around a steady nonlinear mean flow. Such behavior is the basis for further development of downwash correction methods.The correction of pressure distributions through the weighting of the lifting surface self-induced downwash is also known as downwash weighting method. This method has been enhanced leading to a new downwash correction technique. The procedure may be divided in two steps, where the first step is a nonlinear steady mean flow correction, with nonlinear pressure differences considered as reference conditions to correct the self induced downwash. The second step is the correction of the unsteady component of the downwash, where the corresponding reference unsteady pressure differences are predicted by a linear aerodynamic model, based on the potential flow equations.This extended downwash correction method led to a rational formulation named as "successive kernel expansion method" (SKEM). The unsteady pressures and aeroelastic stability boundaries computations using such method led to good agreement with experimental measurements. This procedure is a rapid form to compute the transonic flutter speed boundaries, compared to computational aeroelasticity and experimental techniques. |
id |
ITA_5fc6c8752a5fd8a2d1ae1b43529153e6 |
---|---|
oai_identifier_str |
oai:agregador.ibict.br.BDTD_ITA:oai:ita.br:29 |
network_acronym_str |
ITA |
network_name_str |
Biblioteca Digital de Teses e Dissertações do ITA |
spelling |
A study on correction methods for aeroelastic analysis in transonic flow.AeroelasticidadeAerodinâmica não-estacionáriaEscoamento transônicoModelos matemáticosCorreçãoDinâmica dos fluidos computacionalSustentação aerodinâmicaMecânica dos fluidosFísicaThe work presents a study of correction techniques to compute unsteady transonic pressure distributions and aeroelastic stability in this flow regime. The methodologies herein investigated are based on corrections of pressure distributions by the weighting of the lifting surface self-induced downwash, resulting from aeroelastic structural displacements or prescribed motions. A number approaches were investigated. An investigation into the linear/nonlinear behavior of unsteady transonic flows was also conducted. It was concluded from such investigation that unsteady transonic flows present a linear behavior with respect to small aeroelastic structural displacements around a steady nonlinear mean flow. Such behavior is the basis for further development of downwash correction methods.The correction of pressure distributions through the weighting of the lifting surface self-induced downwash is also known as downwash weighting method. This method has been enhanced leading to a new downwash correction technique. The procedure may be divided in two steps, where the first step is a nonlinear steady mean flow correction, with nonlinear pressure differences considered as reference conditions to correct the self induced downwash. The second step is the correction of the unsteady component of the downwash, where the corresponding reference unsteady pressure differences are predicted by a linear aerodynamic model, based on the potential flow equations.This extended downwash correction method led to a rational formulation named as "successive kernel expansion method" (SKEM). The unsteady pressures and aeroelastic stability boundaries computations using such method led to good agreement with experimental measurements. This procedure is a rapid form to compute the transonic flutter speed boundaries, compared to computational aeroelasticity and experimental techniques. Instituto Tecnológico de AeronáuticaJoão Luiz Filgueiras de AzevedoOlympio Achilles de Faria MelloRoberto Gil Annes da Silva2004-00-00info:eu-repo/semantics/publishedVersioninfo:eu-repo/semantics/doctoralThesishttp://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=29reponame:Biblioteca Digital de Teses e Dissertações do ITAinstname:Instituto Tecnológico de Aeronáuticainstacron:ITAenginfo:eu-repo/semantics/openAccessapplication/pdf2019-02-02T14:01:37Zoai:agregador.ibict.br.BDTD_ITA:oai:ita.br:29http://oai.bdtd.ibict.br/requestopendoar:null2020-05-28 19:32:01.302Biblioteca Digital de Teses e Dissertações do ITA - Instituto Tecnológico de Aeronáuticatrue |
dc.title.none.fl_str_mv |
A study on correction methods for aeroelastic analysis in transonic flow. |
title |
A study on correction methods for aeroelastic analysis in transonic flow. |
spellingShingle |
A study on correction methods for aeroelastic analysis in transonic flow. Roberto Gil Annes da Silva Aeroelasticidade Aerodinâmica não-estacionária Escoamento transônico Modelos matemáticos Correção Dinâmica dos fluidos computacional Sustentação aerodinâmica Mecânica dos fluidos Física |
title_short |
A study on correction methods for aeroelastic analysis in transonic flow. |
title_full |
A study on correction methods for aeroelastic analysis in transonic flow. |
title_fullStr |
A study on correction methods for aeroelastic analysis in transonic flow. |
title_full_unstemmed |
A study on correction methods for aeroelastic analysis in transonic flow. |
title_sort |
A study on correction methods for aeroelastic analysis in transonic flow. |
author |
Roberto Gil Annes da Silva |
author_facet |
Roberto Gil Annes da Silva |
author_role |
author |
dc.contributor.none.fl_str_mv |
João Luiz Filgueiras de Azevedo Olympio Achilles de Faria Mello |
dc.contributor.author.fl_str_mv |
Roberto Gil Annes da Silva |
dc.subject.por.fl_str_mv |
Aeroelasticidade Aerodinâmica não-estacionária Escoamento transônico Modelos matemáticos Correção Dinâmica dos fluidos computacional Sustentação aerodinâmica Mecânica dos fluidos Física |
topic |
Aeroelasticidade Aerodinâmica não-estacionária Escoamento transônico Modelos matemáticos Correção Dinâmica dos fluidos computacional Sustentação aerodinâmica Mecânica dos fluidos Física |
dc.description.none.fl_txt_mv |
The work presents a study of correction techniques to compute unsteady transonic pressure distributions and aeroelastic stability in this flow regime. The methodologies herein investigated are based on corrections of pressure distributions by the weighting of the lifting surface self-induced downwash, resulting from aeroelastic structural displacements or prescribed motions. A number approaches were investigated. An investigation into the linear/nonlinear behavior of unsteady transonic flows was also conducted. It was concluded from such investigation that unsteady transonic flows present a linear behavior with respect to small aeroelastic structural displacements around a steady nonlinear mean flow. Such behavior is the basis for further development of downwash correction methods.The correction of pressure distributions through the weighting of the lifting surface self-induced downwash is also known as downwash weighting method. This method has been enhanced leading to a new downwash correction technique. The procedure may be divided in two steps, where the first step is a nonlinear steady mean flow correction, with nonlinear pressure differences considered as reference conditions to correct the self induced downwash. The second step is the correction of the unsteady component of the downwash, where the corresponding reference unsteady pressure differences are predicted by a linear aerodynamic model, based on the potential flow equations.This extended downwash correction method led to a rational formulation named as "successive kernel expansion method" (SKEM). The unsteady pressures and aeroelastic stability boundaries computations using such method led to good agreement with experimental measurements. This procedure is a rapid form to compute the transonic flutter speed boundaries, compared to computational aeroelasticity and experimental techniques. |
description |
The work presents a study of correction techniques to compute unsteady transonic pressure distributions and aeroelastic stability in this flow regime. The methodologies herein investigated are based on corrections of pressure distributions by the weighting of the lifting surface self-induced downwash, resulting from aeroelastic structural displacements or prescribed motions. A number approaches were investigated. An investigation into the linear/nonlinear behavior of unsteady transonic flows was also conducted. It was concluded from such investigation that unsteady transonic flows present a linear behavior with respect to small aeroelastic structural displacements around a steady nonlinear mean flow. Such behavior is the basis for further development of downwash correction methods.The correction of pressure distributions through the weighting of the lifting surface self-induced downwash is also known as downwash weighting method. This method has been enhanced leading to a new downwash correction technique. The procedure may be divided in two steps, where the first step is a nonlinear steady mean flow correction, with nonlinear pressure differences considered as reference conditions to correct the self induced downwash. The second step is the correction of the unsteady component of the downwash, where the corresponding reference unsteady pressure differences are predicted by a linear aerodynamic model, based on the potential flow equations.This extended downwash correction method led to a rational formulation named as "successive kernel expansion method" (SKEM). The unsteady pressures and aeroelastic stability boundaries computations using such method led to good agreement with experimental measurements. This procedure is a rapid form to compute the transonic flutter speed boundaries, compared to computational aeroelasticity and experimental techniques. |
publishDate |
2004 |
dc.date.none.fl_str_mv |
2004-00-00 |
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=29 |
url |
http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=29 |
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 |
Aeroelasticidade Aerodinâmica não-estacionária Escoamento transônico Modelos matemáticos Correção Dinâmica dos fluidos computacional Sustentação aerodinâmica Mecânica dos fluidos Física |
_version_ |
1706809252314611712 |