Experimental analyisis of a hypersonic waverider.
Autor(a) principal: | |
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Data de Publicação: | 2009 |
Tipo de documento: | Dissertação |
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=796 |
Resumo: | This work presents the results of shock tunnel tests of a Mach 10 waverider with sharp leading edges. The waverider surface was generated from a conical flowfield with the volume and the viscous lift-to-drag ratio as optimization parameters. A compression and expansion ramps were added to the pure waverider surface in order to simulate the flow over a scramjet engine. The compression ramp was designed so as to provide the ideal conditions for the supersonic combustion of the Hydrogen while the expansion section was derived from an ideal minimum length supersonic nozzle. The experimental data included Schlieren photographs of the flow and the pressure distribution over the compression surface. These data were compared with the inviscid theory. During these investigations, the IEAv's T3 shock tunnel was used to simulate the hypersonic flow. The stagnation conditions as well as the free stream properties were estimated using numerical codes. The tunnel operated at Mach number ranges of 8.9 to 10, Reynolds number from 2.25 x 106 to 8.76 x 106 (m-1) and Knudsen number from 0.06 to 0.19. From the Schlieren photographs it was noted that the inlet flowfield behaves according to the predictions of the hypersonic viscous interaction models. Also, the pressure variation along the compression surface centerline was obtained using piezoelectric pressure sensors. The resulted profile presented the general trend of the flow described by these models. |
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Biblioteca Digital de Teses e Dissertações do ITA |
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Experimental analyisis of a hypersonic waverider.Veículos de sustentação por ondas de choqueVeículos aeroespaciaisConfigurações aerodinâmicasEscoamento hipersônicoDinâmica dos fluidosAerodinâmicaEngenharia aeroespacialThis work presents the results of shock tunnel tests of a Mach 10 waverider with sharp leading edges. The waverider surface was generated from a conical flowfield with the volume and the viscous lift-to-drag ratio as optimization parameters. A compression and expansion ramps were added to the pure waverider surface in order to simulate the flow over a scramjet engine. The compression ramp was designed so as to provide the ideal conditions for the supersonic combustion of the Hydrogen while the expansion section was derived from an ideal minimum length supersonic nozzle. The experimental data included Schlieren photographs of the flow and the pressure distribution over the compression surface. These data were compared with the inviscid theory. During these investigations, the IEAv's T3 shock tunnel was used to simulate the hypersonic flow. The stagnation conditions as well as the free stream properties were estimated using numerical codes. The tunnel operated at Mach number ranges of 8.9 to 10, Reynolds number from 2.25 x 106 to 8.76 x 106 (m-1) and Knudsen number from 0.06 to 0.19. From the Schlieren photographs it was noted that the inlet flowfield behaves according to the predictions of the hypersonic viscous interaction models. Also, the pressure variation along the compression surface centerline was obtained using piezoelectric pressure sensors. The resulted profile presented the general trend of the flow described by these models.Instituto Tecnológico de AeronáuticaMarco Antonio Sala MinucciPaulo Afonso de Oliveira SovieroTiago Cavalcanti Rolim2009-04-08info:eu-repo/semantics/publishedVersioninfo:eu-repo/semantics/masterThesishttp://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=796reponame:Biblioteca Digital de Teses e Dissertações do ITAinstname:Instituto Tecnológico de Aeronáuticainstacron:ITAenginfo:eu-repo/semantics/openAccessapplication/pdf2019-02-02T14:01:55Zoai:agregador.ibict.br.BDTD_ITA:oai:ita.br:796http://oai.bdtd.ibict.br/requestopendoar:null2020-05-28 19:34:24.738Biblioteca Digital de Teses e Dissertações do ITA - Instituto Tecnológico de Aeronáuticatrue |
dc.title.none.fl_str_mv |
Experimental analyisis of a hypersonic waverider. |
title |
Experimental analyisis of a hypersonic waverider. |
spellingShingle |
Experimental analyisis of a hypersonic waverider. Tiago Cavalcanti Rolim Veículos de sustentação por ondas de choque Veículos aeroespaciais Configurações aerodinâmicas Escoamento hipersônico Dinâmica dos fluidos Aerodinâmica Engenharia aeroespacial |
title_short |
Experimental analyisis of a hypersonic waverider. |
title_full |
Experimental analyisis of a hypersonic waverider. |
title_fullStr |
Experimental analyisis of a hypersonic waverider. |
title_full_unstemmed |
Experimental analyisis of a hypersonic waverider. |
title_sort |
Experimental analyisis of a hypersonic waverider. |
author |
Tiago Cavalcanti Rolim |
author_facet |
Tiago Cavalcanti Rolim |
author_role |
author |
dc.contributor.none.fl_str_mv |
Marco Antonio Sala Minucci Paulo Afonso de Oliveira Soviero |
dc.contributor.author.fl_str_mv |
Tiago Cavalcanti Rolim |
dc.subject.por.fl_str_mv |
Veículos de sustentação por ondas de choque Veículos aeroespaciais Configurações aerodinâmicas Escoamento hipersônico Dinâmica dos fluidos Aerodinâmica Engenharia aeroespacial |
topic |
Veículos de sustentação por ondas de choque Veículos aeroespaciais Configurações aerodinâmicas Escoamento hipersônico Dinâmica dos fluidos Aerodinâmica Engenharia aeroespacial |
dc.description.none.fl_txt_mv |
This work presents the results of shock tunnel tests of a Mach 10 waverider with sharp leading edges. The waverider surface was generated from a conical flowfield with the volume and the viscous lift-to-drag ratio as optimization parameters. A compression and expansion ramps were added to the pure waverider surface in order to simulate the flow over a scramjet engine. The compression ramp was designed so as to provide the ideal conditions for the supersonic combustion of the Hydrogen while the expansion section was derived from an ideal minimum length supersonic nozzle. The experimental data included Schlieren photographs of the flow and the pressure distribution over the compression surface. These data were compared with the inviscid theory. During these investigations, the IEAv's T3 shock tunnel was used to simulate the hypersonic flow. The stagnation conditions as well as the free stream properties were estimated using numerical codes. The tunnel operated at Mach number ranges of 8.9 to 10, Reynolds number from 2.25 x 106 to 8.76 x 106 (m-1) and Knudsen number from 0.06 to 0.19. From the Schlieren photographs it was noted that the inlet flowfield behaves according to the predictions of the hypersonic viscous interaction models. Also, the pressure variation along the compression surface centerline was obtained using piezoelectric pressure sensors. The resulted profile presented the general trend of the flow described by these models. |
description |
This work presents the results of shock tunnel tests of a Mach 10 waverider with sharp leading edges. The waverider surface was generated from a conical flowfield with the volume and the viscous lift-to-drag ratio as optimization parameters. A compression and expansion ramps were added to the pure waverider surface in order to simulate the flow over a scramjet engine. The compression ramp was designed so as to provide the ideal conditions for the supersonic combustion of the Hydrogen while the expansion section was derived from an ideal minimum length supersonic nozzle. The experimental data included Schlieren photographs of the flow and the pressure distribution over the compression surface. These data were compared with the inviscid theory. During these investigations, the IEAv's T3 shock tunnel was used to simulate the hypersonic flow. The stagnation conditions as well as the free stream properties were estimated using numerical codes. The tunnel operated at Mach number ranges of 8.9 to 10, Reynolds number from 2.25 x 106 to 8.76 x 106 (m-1) and Knudsen number from 0.06 to 0.19. From the Schlieren photographs it was noted that the inlet flowfield behaves according to the predictions of the hypersonic viscous interaction models. Also, the pressure variation along the compression surface centerline was obtained using piezoelectric pressure sensors. The resulted profile presented the general trend of the flow described by these models. |
publishDate |
2009 |
dc.date.none.fl_str_mv |
2009-04-08 |
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=796 |
url |
http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=796 |
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 |
Veículos de sustentação por ondas de choque Veículos aeroespaciais Configurações aerodinâmicas Escoamento hipersônico Dinâmica dos fluidos Aerodinâmica Engenharia aeroespacial |
_version_ |
1706809262565490688 |