Experimental results from the sounding vehicle Sonda III test campaign in the Pilot Transonic Wind Tunnel
Autor(a) principal: | |
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Data de Publicação: | 2011 |
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=S2175-91462011000300311 |
Resumo: | Abstract: The Pilot Transonic Wind Tunnel of the Institute of Aeronautics and Space has conducted the first test campaign of a sounding vehicle, Sonda III. The campaign is part of a project whose activities and final results are presented in this paper. During the test campaign, many activities were performed to increase the productivity and accuracy of the tunnel. These activities included calibration procedures, corrective and preventive trials, development of auxiliary devices, and theoretical and experimental analysis. Two tasks are described in details: the development and tests performed with the static pressure probe and the automatic re-entry flap actuation system. Several tests were carried out with the Sonda III at Mach numbers ranging from 0.3 to 1.0, at stagnation pressures of 70, 94, and 110 kPa. Experimental results include global aerodynamic coefficients (using internal balance) and pressure distribution over essential regions of the test article (using pressure sensitive paint technique). |
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Experimental results from the sounding vehicle Sonda III test campaign in the Pilot Transonic Wind TunnelAerodynamicsExperimental resultsSonda IIITransonic Wind TunnelAbstract: The Pilot Transonic Wind Tunnel of the Institute of Aeronautics and Space has conducted the first test campaign of a sounding vehicle, Sonda III. The campaign is part of a project whose activities and final results are presented in this paper. During the test campaign, many activities were performed to increase the productivity and accuracy of the tunnel. These activities included calibration procedures, corrective and preventive trials, development of auxiliary devices, and theoretical and experimental analysis. Two tasks are described in details: the development and tests performed with the static pressure probe and the automatic re-entry flap actuation system. Several tests were carried out with the Sonda III at Mach numbers ranging from 0.3 to 1.0, at stagnation pressures of 70, 94, and 110 kPa. Experimental results include global aerodynamic coefficients (using internal balance) and pressure distribution over essential regions of the test article (using pressure sensitive paint technique).Departamento de Ciência e Tecnologia Aeroespacial2011-12-01info:eu-repo/semantics/articleinfo:eu-repo/semantics/publishedVersiontext/htmlhttp://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462011000300311Journal of Aerospace Technology and Management v.3 n.3 2011reponame:Journal of Aerospace Technology and Management (Online)instname:Departamento de Ciência e Tecnologia Aeroespacial (DCTA)instacron:DCTA10.5028/jatm.2011.03033111info:eu-repo/semantics/openAccessFalcão Filho,João Batista P.Reis,Maria Luísa Collucci C.Morgenstern Jr.,Algacyreng2017-05-18T00:00:00Zoai:scielo:S2175-91462011000300311Revistahttp://www.jatm.com.br/ONGhttps://old.scielo.br/oai/scielo-oai.php||secretary@jatm.com.br2175-91461984-9648opendoar:2017-05-18T00:00Journal of Aerospace Technology and Management (Online) - Departamento de Ciência e Tecnologia Aeroespacial (DCTA)false |
dc.title.none.fl_str_mv |
Experimental results from the sounding vehicle Sonda III test campaign in the Pilot Transonic Wind Tunnel |
title |
Experimental results from the sounding vehicle Sonda III test campaign in the Pilot Transonic Wind Tunnel |
spellingShingle |
Experimental results from the sounding vehicle Sonda III test campaign in the Pilot Transonic Wind Tunnel Falcão Filho,João Batista P. Aerodynamics Experimental results Sonda III Transonic Wind Tunnel |
title_short |
Experimental results from the sounding vehicle Sonda III test campaign in the Pilot Transonic Wind Tunnel |
title_full |
Experimental results from the sounding vehicle Sonda III test campaign in the Pilot Transonic Wind Tunnel |
title_fullStr |
Experimental results from the sounding vehicle Sonda III test campaign in the Pilot Transonic Wind Tunnel |
title_full_unstemmed |
Experimental results from the sounding vehicle Sonda III test campaign in the Pilot Transonic Wind Tunnel |
title_sort |
Experimental results from the sounding vehicle Sonda III test campaign in the Pilot Transonic Wind Tunnel |
author |
Falcão Filho,João Batista P. |
author_facet |
Falcão Filho,João Batista P. Reis,Maria Luísa Collucci C. Morgenstern Jr.,Algacyr |
author_role |
author |
author2 |
Reis,Maria Luísa Collucci C. Morgenstern Jr.,Algacyr |
author2_role |
author author |
dc.contributor.author.fl_str_mv |
Falcão Filho,João Batista P. Reis,Maria Luísa Collucci C. Morgenstern Jr.,Algacyr |
dc.subject.por.fl_str_mv |
Aerodynamics Experimental results Sonda III Transonic Wind Tunnel |
topic |
Aerodynamics Experimental results Sonda III Transonic Wind Tunnel |
description |
Abstract: The Pilot Transonic Wind Tunnel of the Institute of Aeronautics and Space has conducted the first test campaign of a sounding vehicle, Sonda III. The campaign is part of a project whose activities and final results are presented in this paper. During the test campaign, many activities were performed to increase the productivity and accuracy of the tunnel. These activities included calibration procedures, corrective and preventive trials, development of auxiliary devices, and theoretical and experimental analysis. Two tasks are described in details: the development and tests performed with the static pressure probe and the automatic re-entry flap actuation system. Several tests were carried out with the Sonda III at Mach numbers ranging from 0.3 to 1.0, at stagnation pressures of 70, 94, and 110 kPa. Experimental results include global aerodynamic coefficients (using internal balance) and pressure distribution over essential regions of the test article (using pressure sensitive paint technique). |
publishDate |
2011 |
dc.date.none.fl_str_mv |
2011-12-01 |
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=S2175-91462011000300311 |
url |
http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462011000300311 |
dc.language.iso.fl_str_mv |
eng |
language |
eng |
dc.relation.none.fl_str_mv |
10.5028/jatm.2011.03033111 |
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.3 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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1754732530482806784 |