Aerothermodynamic Optimization of Aerospace Plane Airfoil Leading Edge
Autor(a) principal: | |
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Data de Publicação: | 2017 |
Outros Autores: | , , |
Tipo de documento: | Artigo |
Idioma: | eng |
Título da fonte: | Journal of Aerospace Technology and Management (Online) |
Texto Completo: | http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462017000400503 |
Resumo: | ABSTRACT: Aiming to mitigate the aerodynamic heating during hypersonic re-entry, the aerothermodynamic optimization of aerospace plane airfoil leading edge is conducted. Lift-to-drag ratio at landing condition is taken as a constraint to ensure the landing aerodynamic performance. First, airfoil profile is parametrically described to be more advantageous during the optimization process, and the Hicks-Henne type function is improved considering its application on the airfoil leading edge. Computational Fluid Dynamics models at hypersonic as well as landing conditions are then established and discussed. Design of Experiment technique is utilized to establish the surrogate model. Afterwards, the previously mentioned surrogate model is employed in combination with the Multi-Island Genetic Algorithm to perform the optimization procedure. NACA 0012 is taken as the baseline airfoil for case study. The results show that the peak heat flux of the optimal airfoil during hypersonic flight is reduced by 7.61% at the stagnation point, while the lift-to-drag remains almost unchanged under landing condition. |
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Journal of Aerospace Technology and Management (Online) |
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Aerothermodynamic Optimization of Aerospace Plane Airfoil Leading EdgeAirfoil optimizationAerodynamic heatingHicks-Henne type functionAirfoil parameterizationSurrogate modelABSTRACT: Aiming to mitigate the aerodynamic heating during hypersonic re-entry, the aerothermodynamic optimization of aerospace plane airfoil leading edge is conducted. Lift-to-drag ratio at landing condition is taken as a constraint to ensure the landing aerodynamic performance. First, airfoil profile is parametrically described to be more advantageous during the optimization process, and the Hicks-Henne type function is improved considering its application on the airfoil leading edge. Computational Fluid Dynamics models at hypersonic as well as landing conditions are then established and discussed. Design of Experiment technique is utilized to establish the surrogate model. Afterwards, the previously mentioned surrogate model is employed in combination with the Multi-Island Genetic Algorithm to perform the optimization procedure. NACA 0012 is taken as the baseline airfoil for case study. The results show that the peak heat flux of the optimal airfoil during hypersonic flight is reduced by 7.61% at the stagnation point, while the lift-to-drag remains almost unchanged under landing condition.Departamento de Ciência e Tecnologia Aeroespacial2017-12-01info:eu-repo/semantics/articleinfo:eu-repo/semantics/publishedVersiontext/htmlhttp://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462017000400503Journal of Aerospace Technology and Management v.9 n.4 2017reponame:Journal of Aerospace Technology and Management (Online)instname:Departamento de Ciência e Tecnologia Aeroespacial (DCTA)instacron:DCTA10.5028/jatm.v9i4.820info:eu-repo/semantics/openAccessZhou,ChenWang,ZhijinZhi,JiaoyangKretov,Anatoliieng2017-10-17T00:00:00Zoai:scielo:S2175-91462017000400503Revistahttp://www.jatm.com.br/ONGhttps://old.scielo.br/oai/scielo-oai.php||secretary@jatm.com.br2175-91461984-9648opendoar:2017-10-17T00:00Journal of Aerospace Technology and Management (Online) - Departamento de Ciência e Tecnologia Aeroespacial (DCTA)false |
dc.title.none.fl_str_mv |
Aerothermodynamic Optimization of Aerospace Plane Airfoil Leading Edge |
title |
Aerothermodynamic Optimization of Aerospace Plane Airfoil Leading Edge |
spellingShingle |
Aerothermodynamic Optimization of Aerospace Plane Airfoil Leading Edge Zhou,Chen Airfoil optimization Aerodynamic heating Hicks-Henne type function Airfoil parameterization Surrogate model |
title_short |
Aerothermodynamic Optimization of Aerospace Plane Airfoil Leading Edge |
title_full |
Aerothermodynamic Optimization of Aerospace Plane Airfoil Leading Edge |
title_fullStr |
Aerothermodynamic Optimization of Aerospace Plane Airfoil Leading Edge |
title_full_unstemmed |
Aerothermodynamic Optimization of Aerospace Plane Airfoil Leading Edge |
title_sort |
Aerothermodynamic Optimization of Aerospace Plane Airfoil Leading Edge |
author |
Zhou,Chen |
author_facet |
Zhou,Chen Wang,Zhijin Zhi,Jiaoyang Kretov,Anatolii |
author_role |
author |
author2 |
Wang,Zhijin Zhi,Jiaoyang Kretov,Anatolii |
author2_role |
author author author |
dc.contributor.author.fl_str_mv |
Zhou,Chen Wang,Zhijin Zhi,Jiaoyang Kretov,Anatolii |
dc.subject.por.fl_str_mv |
Airfoil optimization Aerodynamic heating Hicks-Henne type function Airfoil parameterization Surrogate model |
topic |
Airfoil optimization Aerodynamic heating Hicks-Henne type function Airfoil parameterization Surrogate model |
description |
ABSTRACT: Aiming to mitigate the aerodynamic heating during hypersonic re-entry, the aerothermodynamic optimization of aerospace plane airfoil leading edge is conducted. Lift-to-drag ratio at landing condition is taken as a constraint to ensure the landing aerodynamic performance. First, airfoil profile is parametrically described to be more advantageous during the optimization process, and the Hicks-Henne type function is improved considering its application on the airfoil leading edge. Computational Fluid Dynamics models at hypersonic as well as landing conditions are then established and discussed. Design of Experiment technique is utilized to establish the surrogate model. Afterwards, the previously mentioned surrogate model is employed in combination with the Multi-Island Genetic Algorithm to perform the optimization procedure. NACA 0012 is taken as the baseline airfoil for case study. The results show that the peak heat flux of the optimal airfoil during hypersonic flight is reduced by 7.61% at the stagnation point, while the lift-to-drag remains almost unchanged under landing condition. |
publishDate |
2017 |
dc.date.none.fl_str_mv |
2017-12-01 |
dc.type.driver.fl_str_mv |
info:eu-repo/semantics/article |
dc.type.status.fl_str_mv |
info:eu-repo/semantics/publishedVersion |
format |
article |
status_str |
publishedVersion |
dc.identifier.uri.fl_str_mv |
http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462017000400503 |
url |
http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462017000400503 |
dc.language.iso.fl_str_mv |
eng |
language |
eng |
dc.relation.none.fl_str_mv |
10.5028/jatm.v9i4.820 |
dc.rights.driver.fl_str_mv |
info:eu-repo/semantics/openAccess |
eu_rights_str_mv |
openAccess |
dc.format.none.fl_str_mv |
text/html |
dc.publisher.none.fl_str_mv |
Departamento de Ciência e Tecnologia Aeroespacial |
publisher.none.fl_str_mv |
Departamento de Ciência e Tecnologia Aeroespacial |
dc.source.none.fl_str_mv |
Journal of Aerospace Technology and Management v.9 n.4 2017 reponame:Journal of Aerospace Technology and Management (Online) instname:Departamento de Ciência e Tecnologia Aeroespacial (DCTA) instacron:DCTA |
instname_str |
Departamento de Ciência e Tecnologia Aeroespacial (DCTA) |
instacron_str |
DCTA |
institution |
DCTA |
reponame_str |
Journal of Aerospace Technology and Management (Online) |
collection |
Journal of Aerospace Technology and Management (Online) |
repository.name.fl_str_mv |
Journal of Aerospace Technology and Management (Online) - Departamento de Ciência e Tecnologia Aeroespacial (DCTA) |
repository.mail.fl_str_mv |
||secretary@jatm.com.br |
_version_ |
1754732531685523456 |