Angle of attack effect in the aerothermodynamics of a hypersonic vehicle with a surface discontinuity of gap type
Autor(a) principal: | |
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Data de Publicação: | 2017 |
Tipo de documento: | Dissertação |
Idioma: | eng |
Título da fonte: | Biblioteca Digital de Teses e Dissertações do INPE |
Texto Completo: | http://urlib.net/sid.inpe.br/mtc-m21b/2017/05.23.23.55 |
Resumo: | The development of hypersonic vehicles has become a topic of interest in recent years, since has made it possible to reach inaccessible places such as orbital flights. The construction of these vehicles must be made with specials materials, and must have an efficient aerodynamic shape to withstand high speeds, high temperatures and significant pressure changes. The study described in this dissertation was undertaken with the objective to investigate the impact of discontinuities present on the surface of hypersonic space vehicles. In pursuit of this goal, computational simulations of a low-density hypersonic flow over a flat plate with a gap has been performed by using the Direct Simulation Monte Carlo method. The simulations provided information about the nature of the flowfield structure and the aerodynamic surface properties on the gap resulting from variations in the length-to-depth (L/H) ratio and variations in the angle of attack. A description of the flowfield properties, such as velocity, density, pressure and temperature, and aerodynamics surface quantities, such as, number flux, heat transfer, pressure and skin friction, were obtained by a numerical method that properly account for non-equilibrium effects in the transition flow regime. Results for a gap defined by L/H ratio of 1, 1/2, 1/3 and 1/4, and flow with angle of attack of 10, 15 and 20 degrees, were compared to those of a flat plate without a gap with zero-degree angle of incidence. The analysis showed that the flow topology inside the gap with incidence is slightly different from that for zero-degree angle of incidence for the L/H ratio investigated. It was found that the maximum values for the heat transfer, pressure and skin friction coefficients inside the gap took place on the gap forward face. It was also found that, maximum values for heat transfer coefficient inside the gaps increased with increasing the angle of attack $\alpha$. Nevertheless, it was observed that these maximum values are smaller than those observed in a flat-plate without a gap for the corresponding angle of attack. As a result, in terms of pressure, the presence of the gap on the vehicle surface can not be ignored in the vehicle design. |
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info:eu-repo/semantics/publishedVersioninfo:eu-repo/semantics/masterThesisAngle of attack effect in the aerothermodynamics of a hypersonic vehicle with a surface discontinuity of gap typeEfeito do ângulo de ataque na aerotermodinâmica de um veículo hipersônico com descontinuidade na superfície do tipo filete.2017-03-29Wilson Fernando Nogueira dos SantosDenize KalempaPaulo Henrique Mineiro LeiteLuis Carlos Roldan TorresInstituto Nacional de Pesquisas Espaciais (INPE)Programa de Pós-Graduação do INPE em Combustão e PropulsãoINPEBRdirect simulation Monte Carloescoamento hipersônicosescoamento rarefeitofileteveículos hipersônicosdirect simulation Monte Carlohypersonic flowrarefied flowgap flowhypersonic vehicleThe development of hypersonic vehicles has become a topic of interest in recent years, since has made it possible to reach inaccessible places such as orbital flights. The construction of these vehicles must be made with specials materials, and must have an efficient aerodynamic shape to withstand high speeds, high temperatures and significant pressure changes. The study described in this dissertation was undertaken with the objective to investigate the impact of discontinuities present on the surface of hypersonic space vehicles. In pursuit of this goal, computational simulations of a low-density hypersonic flow over a flat plate with a gap has been performed by using the Direct Simulation Monte Carlo method. The simulations provided information about the nature of the flowfield structure and the aerodynamic surface properties on the gap resulting from variations in the length-to-depth (L/H) ratio and variations in the angle of attack. A description of the flowfield properties, such as velocity, density, pressure and temperature, and aerodynamics surface quantities, such as, number flux, heat transfer, pressure and skin friction, were obtained by a numerical method that properly account for non-equilibrium effects in the transition flow regime. Results for a gap defined by L/H ratio of 1, 1/2, 1/3 and 1/4, and flow with angle of attack of 10, 15 and 20 degrees, were compared to those of a flat plate without a gap with zero-degree angle of incidence. The analysis showed that the flow topology inside the gap with incidence is slightly different from that for zero-degree angle of incidence for the L/H ratio investigated. It was found that the maximum values for the heat transfer, pressure and skin friction coefficients inside the gap took place on the gap forward face. It was also found that, maximum values for heat transfer coefficient inside the gaps increased with increasing the angle of attack $\alpha$. Nevertheless, it was observed that these maximum values are smaller than those observed in a flat-plate without a gap for the corresponding angle of attack. As a result, in terms of pressure, the presence of the gap on the vehicle surface can not be ignored in the vehicle design.O desenvolvimento de veículos hipersônicos tem se tornado um tema de interesse nos últimos anos, considerando-se a possibilidade de se chegar com tais veículos a locais até então inacessíveis como os voos orbitais. A construção desses veículos exige materiais especiais e deve apresentar uma forma aerodinâmica eficiente para resistir altas velocidades além de temperaturas elevadas e mudanças de pressão significativas. O estudo descrito nesta dissertação foi realizado com o objetivo de investigar o impacto de descontinuidades presentes na superfície de veículos espaciais hipersônicos. Em busca deste objetivo, simulações computacionais de um escoamento hipersônico rarefeito sobre uma placa plana, foi realizada usando-se o método Direct Simulation Monte Carlo. As simulações forneceram informações sobre a natureza da estrutura do escoamento, propriedades primarias e propriedades aerodinâmicas, devido a variações na razão comprimento-profundidade (L/H), e variações no ângulo de ataque. Uma descrição das propriedades primarias, tais como velocidade, massa específica, pressão e temperatura, e das quantidades aerodinâmica, tais como transferência de calor, pressão e atrito na superfície, foi obtida por um método numérico que leva em conta os efeitos de não-equilíbrio no regime de transição. Os resultados para um filete definido por uma razão L/H de 1, 1/2, 1/3 e 1/4, e com ângulo de ataque do escoamento de 10, 15 e 20 graus, foram comparados com os de uma placa plana sem a presença de um filete. A análise mostrou que a estrutura do escoamento dentro do filete com ângulo de ataque é ligeiramente diferente daquela com zero grau de incidência para cada razão L/H investigada. Verificou-se que os valores máximos para os coeficientes de transferência de calor, pressão e coeficiente de atrito ocorreram na superfície a montante do escoamento dentro do filete. Verificou-se também que, os valores máximos para o coeficiente de transferência de calor dentro do filete aumentaram com o aumento do ângulo de ataque $\alpha$. Como resultado, em termos de pressão, a presença do filete sobre a superfície do veículo não pode ser ignorada no projeto do veículo.http://urlib.net/sid.inpe.br/mtc-m21b/2017/05.23.23.55info:eu-repo/semantics/openAccessengreponame:Biblioteca Digital de Teses e Dissertações do INPEinstname:Instituto Nacional de Pesquisas Espaciais (INPE)instacron:INPE2021-07-31T06:55:25Zoai:urlib.net:sid.inpe.br/mtc-m21b/2017/05.23.23.55.19-0Biblioteca Digital de Teses e Dissertaçõeshttp://bibdigital.sid.inpe.br/PUBhttp://bibdigital.sid.inpe.br/col/iconet.com.br/banon/2003/11.21.21.08/doc/oai.cgiopendoar:32772021-07-31 06:55:25.993Biblioteca Digital de Teses e Dissertações do INPE - Instituto Nacional de Pesquisas Espaciais (INPE)false |
dc.title.en.fl_str_mv |
Angle of attack effect in the aerothermodynamics of a hypersonic vehicle with a surface discontinuity of gap type |
dc.title.alternative.pt.fl_str_mv |
Efeito do ângulo de ataque na aerotermodinâmica de um veículo hipersônico com descontinuidade na superfície do tipo filete. |
title |
Angle of attack effect in the aerothermodynamics of a hypersonic vehicle with a surface discontinuity of gap type |
spellingShingle |
Angle of attack effect in the aerothermodynamics of a hypersonic vehicle with a surface discontinuity of gap type Luis Carlos Roldan Torres |
title_short |
Angle of attack effect in the aerothermodynamics of a hypersonic vehicle with a surface discontinuity of gap type |
title_full |
Angle of attack effect in the aerothermodynamics of a hypersonic vehicle with a surface discontinuity of gap type |
title_fullStr |
Angle of attack effect in the aerothermodynamics of a hypersonic vehicle with a surface discontinuity of gap type |
title_full_unstemmed |
Angle of attack effect in the aerothermodynamics of a hypersonic vehicle with a surface discontinuity of gap type |
title_sort |
Angle of attack effect in the aerothermodynamics of a hypersonic vehicle with a surface discontinuity of gap type |
author |
Luis Carlos Roldan Torres |
author_facet |
Luis Carlos Roldan Torres |
author_role |
author |
dc.contributor.advisor1.fl_str_mv |
Wilson Fernando Nogueira dos Santos |
dc.contributor.referee1.fl_str_mv |
Denize Kalempa |
dc.contributor.referee2.fl_str_mv |
Paulo Henrique Mineiro Leite |
dc.contributor.author.fl_str_mv |
Luis Carlos Roldan Torres |
contributor_str_mv |
Wilson Fernando Nogueira dos Santos Denize Kalempa Paulo Henrique Mineiro Leite |
dc.description.abstract.por.fl_txt_mv |
The development of hypersonic vehicles has become a topic of interest in recent years, since has made it possible to reach inaccessible places such as orbital flights. The construction of these vehicles must be made with specials materials, and must have an efficient aerodynamic shape to withstand high speeds, high temperatures and significant pressure changes. The study described in this dissertation was undertaken with the objective to investigate the impact of discontinuities present on the surface of hypersonic space vehicles. In pursuit of this goal, computational simulations of a low-density hypersonic flow over a flat plate with a gap has been performed by using the Direct Simulation Monte Carlo method. The simulations provided information about the nature of the flowfield structure and the aerodynamic surface properties on the gap resulting from variations in the length-to-depth (L/H) ratio and variations in the angle of attack. A description of the flowfield properties, such as velocity, density, pressure and temperature, and aerodynamics surface quantities, such as, number flux, heat transfer, pressure and skin friction, were obtained by a numerical method that properly account for non-equilibrium effects in the transition flow regime. Results for a gap defined by L/H ratio of 1, 1/2, 1/3 and 1/4, and flow with angle of attack of 10, 15 and 20 degrees, were compared to those of a flat plate without a gap with zero-degree angle of incidence. The analysis showed that the flow topology inside the gap with incidence is slightly different from that for zero-degree angle of incidence for the L/H ratio investigated. It was found that the maximum values for the heat transfer, pressure and skin friction coefficients inside the gap took place on the gap forward face. It was also found that, maximum values for heat transfer coefficient inside the gaps increased with increasing the angle of attack $\alpha$. Nevertheless, it was observed that these maximum values are smaller than those observed in a flat-plate without a gap for the corresponding angle of attack. As a result, in terms of pressure, the presence of the gap on the vehicle surface can not be ignored in the vehicle design. O desenvolvimento de veículos hipersônicos tem se tornado um tema de interesse nos últimos anos, considerando-se a possibilidade de se chegar com tais veículos a locais até então inacessíveis como os voos orbitais. A construção desses veículos exige materiais especiais e deve apresentar uma forma aerodinâmica eficiente para resistir altas velocidades além de temperaturas elevadas e mudanças de pressão significativas. O estudo descrito nesta dissertação foi realizado com o objetivo de investigar o impacto de descontinuidades presentes na superfície de veículos espaciais hipersônicos. Em busca deste objetivo, simulações computacionais de um escoamento hipersônico rarefeito sobre uma placa plana, foi realizada usando-se o método Direct Simulation Monte Carlo. As simulações forneceram informações sobre a natureza da estrutura do escoamento, propriedades primarias e propriedades aerodinâmicas, devido a variações na razão comprimento-profundidade (L/H), e variações no ângulo de ataque. Uma descrição das propriedades primarias, tais como velocidade, massa específica, pressão e temperatura, e das quantidades aerodinâmica, tais como transferência de calor, pressão e atrito na superfície, foi obtida por um método numérico que leva em conta os efeitos de não-equilíbrio no regime de transição. Os resultados para um filete definido por uma razão L/H de 1, 1/2, 1/3 e 1/4, e com ângulo de ataque do escoamento de 10, 15 e 20 graus, foram comparados com os de uma placa plana sem a presença de um filete. A análise mostrou que a estrutura do escoamento dentro do filete com ângulo de ataque é ligeiramente diferente daquela com zero grau de incidência para cada razão L/H investigada. Verificou-se que os valores máximos para os coeficientes de transferência de calor, pressão e coeficiente de atrito ocorreram na superfície a montante do escoamento dentro do filete. Verificou-se também que, os valores máximos para o coeficiente de transferência de calor dentro do filete aumentaram com o aumento do ângulo de ataque $\alpha$. Como resultado, em termos de pressão, a presença do filete sobre a superfície do veículo não pode ser ignorada no projeto do veículo. |
description |
The development of hypersonic vehicles has become a topic of interest in recent years, since has made it possible to reach inaccessible places such as orbital flights. The construction of these vehicles must be made with specials materials, and must have an efficient aerodynamic shape to withstand high speeds, high temperatures and significant pressure changes. The study described in this dissertation was undertaken with the objective to investigate the impact of discontinuities present on the surface of hypersonic space vehicles. In pursuit of this goal, computational simulations of a low-density hypersonic flow over a flat plate with a gap has been performed by using the Direct Simulation Monte Carlo method. The simulations provided information about the nature of the flowfield structure and the aerodynamic surface properties on the gap resulting from variations in the length-to-depth (L/H) ratio and variations in the angle of attack. A description of the flowfield properties, such as velocity, density, pressure and temperature, and aerodynamics surface quantities, such as, number flux, heat transfer, pressure and skin friction, were obtained by a numerical method that properly account for non-equilibrium effects in the transition flow regime. Results for a gap defined by L/H ratio of 1, 1/2, 1/3 and 1/4, and flow with angle of attack of 10, 15 and 20 degrees, were compared to those of a flat plate without a gap with zero-degree angle of incidence. The analysis showed that the flow topology inside the gap with incidence is slightly different from that for zero-degree angle of incidence for the L/H ratio investigated. It was found that the maximum values for the heat transfer, pressure and skin friction coefficients inside the gap took place on the gap forward face. It was also found that, maximum values for heat transfer coefficient inside the gaps increased with increasing the angle of attack $\alpha$. Nevertheless, it was observed that these maximum values are smaller than those observed in a flat-plate without a gap for the corresponding angle of attack. As a result, in terms of pressure, the presence of the gap on the vehicle surface can not be ignored in the vehicle design. |
publishDate |
2017 |
dc.date.issued.fl_str_mv |
2017-03-29 |
dc.type.status.fl_str_mv |
info:eu-repo/semantics/publishedVersion |
dc.type.driver.fl_str_mv |
info:eu-repo/semantics/masterThesis |
status_str |
publishedVersion |
format |
masterThesis |
dc.identifier.uri.fl_str_mv |
http://urlib.net/sid.inpe.br/mtc-m21b/2017/05.23.23.55 |
url |
http://urlib.net/sid.inpe.br/mtc-m21b/2017/05.23.23.55 |
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.publisher.none.fl_str_mv |
Instituto Nacional de Pesquisas Espaciais (INPE) |
dc.publisher.program.fl_str_mv |
Programa de Pós-Graduação do INPE em Combustão e Propulsão |
dc.publisher.initials.fl_str_mv |
INPE |
dc.publisher.country.fl_str_mv |
BR |
publisher.none.fl_str_mv |
Instituto Nacional de Pesquisas Espaciais (INPE) |
dc.source.none.fl_str_mv |
reponame:Biblioteca Digital de Teses e Dissertações do INPE instname:Instituto Nacional de Pesquisas Espaciais (INPE) instacron:INPE |
reponame_str |
Biblioteca Digital de Teses e Dissertações do INPE |
collection |
Biblioteca Digital de Teses e Dissertações do INPE |
instname_str |
Instituto Nacional de Pesquisas Espaciais (INPE) |
instacron_str |
INPE |
institution |
INPE |
repository.name.fl_str_mv |
Biblioteca Digital de Teses e Dissertações do INPE - Instituto Nacional de Pesquisas Espaciais (INPE) |
repository.mail.fl_str_mv |
|
publisher_program_txtF_mv |
Programa de Pós-Graduação do INPE em Combustão e Propulsão |
contributor_advisor1_txtF_mv |
Wilson Fernando Nogueira dos Santos |
_version_ |
1706809359992881152 |