Experimental results of a Mach 10 conical-flow derived waverider to 14-X hypersonic aerospace vehicle

Detalhes bibliográficos
Autor(a) principal: Rolim,Tiago Cavalcanti
Data de Publicação: 2011
Outros Autores: Toro,Paulo Gilberto de Paula, Minucci,Marco Antonio Sala, Oliveira,Antônio de Carlos de, Follador,Roberto da Cunha
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=S2175-91462011000200127
Resumo: Abstract This paper presents a research in the development of the 14-X hypersonic airspace vehicle at Institute for Advanced Studies (IEAv) from Department of Science and Aerospace Technology (DCTA) of the Brazilian Air Force (FAB). The 14-X project objective is to develop a higher efficient satellite launch alternative, using a Supersonic Combustion Ramjet (SCRAMJET) engine and waverider aerodynamics. For this development, the waverider technology is under investigation in Prof. Henry T. Nagamatsu Aerothermodynamics and Hypersonics Laboratory (LHTN), in IEAv/DCTA. The investigation has been conducted through ground test campaigns in Hypersonic Shock Tunnel T3. The 14-X Waverider Vehicle characteristic was verified in shock tunnel T3 where surface static pressures and pitot pressure for Mach number 10 were measured and, using Schlieren photographs Diagnostic Method, it was possible to identify a leading-edge attached shock wave in 14-X lower surface.
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spelling Experimental results of a Mach 10 conical-flow derived waverider to 14-X hypersonic aerospace vehicleHypersonicsHypersonic systemsShock tunnelSchlierenWaveriderAbstract This paper presents a research in the development of the 14-X hypersonic airspace vehicle at Institute for Advanced Studies (IEAv) from Department of Science and Aerospace Technology (DCTA) of the Brazilian Air Force (FAB). The 14-X project objective is to develop a higher efficient satellite launch alternative, using a Supersonic Combustion Ramjet (SCRAMJET) engine and waverider aerodynamics. For this development, the waverider technology is under investigation in Prof. Henry T. Nagamatsu Aerothermodynamics and Hypersonics Laboratory (LHTN), in IEAv/DCTA. The investigation has been conducted through ground test campaigns in Hypersonic Shock Tunnel T3. The 14-X Waverider Vehicle characteristic was verified in shock tunnel T3 where surface static pressures and pitot pressure for Mach number 10 were measured and, using Schlieren photographs Diagnostic Method, it was possible to identify a leading-edge attached shock wave in 14-X lower surface.Departamento de Ciência e Tecnologia Aeroespacial2011-08-01info:eu-repo/semantics/articleinfo:eu-repo/semantics/publishedVersiontext/htmlhttp://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462011000200127Journal of Aerospace Technology and Management v.3 n.2 2011reponame:Journal of Aerospace Technology and Management (Online)instname:Departamento de Ciência e Tecnologia Aeroespacial (DCTA)instacron:DCTA10.5028/jatm.2011.03027510info:eu-repo/semantics/openAccessRolim,Tiago CavalcantiToro,Paulo Gilberto de PaulaMinucci,Marco Antonio SalaOliveira,Antônio de Carlos deFollador,Roberto da Cunhaeng2017-05-24T00:00:00Zoai:scielo:S2175-91462011000200127Revistahttp://www.jatm.com.br/ONGhttps://old.scielo.br/oai/scielo-oai.php||secretary@jatm.com.br2175-91461984-9648opendoar:2017-05-24T00:00Journal of Aerospace Technology and Management (Online) - Departamento de Ciência e Tecnologia Aeroespacial (DCTA)false
dc.title.none.fl_str_mv Experimental results of a Mach 10 conical-flow derived waverider to 14-X hypersonic aerospace vehicle
title Experimental results of a Mach 10 conical-flow derived waverider to 14-X hypersonic aerospace vehicle
spellingShingle Experimental results of a Mach 10 conical-flow derived waverider to 14-X hypersonic aerospace vehicle
Rolim,Tiago Cavalcanti
Hypersonics
Hypersonic systems
Shock tunnel
Schlieren
Waverider
title_short Experimental results of a Mach 10 conical-flow derived waverider to 14-X hypersonic aerospace vehicle
title_full Experimental results of a Mach 10 conical-flow derived waverider to 14-X hypersonic aerospace vehicle
title_fullStr Experimental results of a Mach 10 conical-flow derived waverider to 14-X hypersonic aerospace vehicle
title_full_unstemmed Experimental results of a Mach 10 conical-flow derived waverider to 14-X hypersonic aerospace vehicle
title_sort Experimental results of a Mach 10 conical-flow derived waverider to 14-X hypersonic aerospace vehicle
author Rolim,Tiago Cavalcanti
author_facet Rolim,Tiago Cavalcanti
Toro,Paulo Gilberto de Paula
Minucci,Marco Antonio Sala
Oliveira,Antônio de Carlos de
Follador,Roberto da Cunha
author_role author
author2 Toro,Paulo Gilberto de Paula
Minucci,Marco Antonio Sala
Oliveira,Antônio de Carlos de
Follador,Roberto da Cunha
author2_role author
author
author
author
dc.contributor.author.fl_str_mv Rolim,Tiago Cavalcanti
Toro,Paulo Gilberto de Paula
Minucci,Marco Antonio Sala
Oliveira,Antônio de Carlos de
Follador,Roberto da Cunha
dc.subject.por.fl_str_mv Hypersonics
Hypersonic systems
Shock tunnel
Schlieren
Waverider
topic Hypersonics
Hypersonic systems
Shock tunnel
Schlieren
Waverider
description Abstract This paper presents a research in the development of the 14-X hypersonic airspace vehicle at Institute for Advanced Studies (IEAv) from Department of Science and Aerospace Technology (DCTA) of the Brazilian Air Force (FAB). The 14-X project objective is to develop a higher efficient satellite launch alternative, using a Supersonic Combustion Ramjet (SCRAMJET) engine and waverider aerodynamics. For this development, the waverider technology is under investigation in Prof. Henry T. Nagamatsu Aerothermodynamics and Hypersonics Laboratory (LHTN), in IEAv/DCTA. The investigation has been conducted through ground test campaigns in Hypersonic Shock Tunnel T3. The 14-X Waverider Vehicle characteristic was verified in shock tunnel T3 where surface static pressures and pitot pressure for Mach number 10 were measured and, using Schlieren photographs Diagnostic Method, it was possible to identify a leading-edge attached shock wave in 14-X lower surface.
publishDate 2011
dc.date.none.fl_str_mv 2011-08-01
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=S2175-91462011000200127
url http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462011000200127
dc.language.iso.fl_str_mv eng
language eng
dc.relation.none.fl_str_mv 10.5028/jatm.2011.03027510
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.3 n.2 2011
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
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