A new approach to optimize the scramjet inlet design applying the total pressure recovery

Detalhes bibliográficos
Autor(a) principal: Fernandes, Alef Giovane Lima do Nascimento
Data de Publicação: 2019
Tipo de documento: Trabalho de conclusão de curso
Idioma: eng
Título da fonte: Repositório Institucional da UFRN
Texto Completo: https://repositorio.ufrn.br/handle/123456789/43011
Resumo: CNPq
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spelling Fernandes, Alef Giovane Lima do NascimentoBorba, Gilvan LuizBessa, Kleiber Lima deMarinho, George Santos2019-12-10T14:03:09Z2021-10-05T15:59:45Z2019-12-10T14:03:09Z2021-10-05T15:59:45Z2019-12-0520180154459FERNANDES, Alef Giovane Lima do Nascimento. A new approach to optimize the scramjet inlet design applying the total pressure recovery. 2019. 9 f. Trabalho de Conclusão de Curso (Graduação em Engenharia Mecânica) - Centro de Tecnologia, Departamento de Engenharia Mecânica, Universidade Federal do Rio Grande do Norte, Natal, 2019.https://repositorio.ufrn.br/handle/123456789/43011CNPqA generic hypersonic airbreathing propulsion based on supersonic combustion ramjet (scramjet) technology has been designed, at the Universidade Federal do Rio Grande do Norte (UFRN), using analytical theoretical analysis (engineering approach). A two-dimensional hydrogen powered generic scramjet inlet has been designed to demonstrate, in atmospheric flight, a supersonic combustion, of atmospheric air (in supersonic speed) with hydrogen, on an acceleration mission to 2050 m/s (Mach number 6.8) at 30 km geometric altitude. In general in a preliminary design, one-dimensional compressible flow (shock wave) theory, which may readily describe many features of compression region of the airbreathing engine, may used to estimate the shock wave angles, thermodynamic properties and the velocities (Mach numbers) of the hypersonic atmospheric air flow, at the generic scramjet inlet. However, the deflection angles of the compression ramps are known. Design and optimization of a 2-D mixed compression generic scramjet models are investigated by the extended Oswatitsch classical optimization of a 2-D supersonic inlet procedure to scramjet inlets. The deflection angles of compression section ramps and the corresponding thermodynamic property ratio (pressure, temperature and specific mass) of the airflow as well as the airflow velocities (and corresponding Mach numbers) are obtained by the present optimization criterion. The present optimization criterion is defined based on the system of (n-1) incident oblique shockwaves, with the equal strength, and one reflected oblique shockwave establish in the external and internal compression section, respectively, which reduce the known hypersonic flow (pressure, temperature, specific mass and flow velocity) to a supersonic flow, with required temperature and velocity, at the entrance of a combustion chamber. Therefore, the maximum shock pressure recovery is obtained as function of the incident oblique shockwaves of equal strength. Thermodynamic property ratio (pressure, temperature and specific mass) as well as the flow velocities (and corresponding Mach numbers) are presented for seven incident oblique shockwaves.Universidade Federal do Rio Grande do NorteUFRNBrasilEngenharia MecânicaEngenharia Mecânica. Fenômenos de Transporte. Mecânica dos Fluidos.Scramjet. Supersonic combustion ramjet. Hypersonic airbreathing propulsion.A new approach to optimize the scramjet inlet design applying the total pressure recoveryinfo:eu-repo/semantics/publishedVersioninfo:eu-repo/semantics/bachelorThesisengreponame:Repositório Institucional da UFRNinstname:Universidade Federal do Rio Grande do Norte (UFRN)instacron:UFRNinfo:eu-repo/semantics/openAccessCC-LICENSElicense_rdfapplication/octet-stream701https://repositorio.ufrn.br/bitstream/123456789/43011/1/license_rdf42fd4ad1e89814f5e4a476b409eb708cMD51TEXTTCC_Alef.pdf.txtExtracted texttext/plain28661https://repositorio.ufrn.br/bitstream/123456789/43011/2/TCC_Alef.pdf.txtb6b9b5ad59c4929dace5b3dbbdddf99cMD52ORIGINALTCC_Alef.pdfA NEW APPROACH TO OPTIMIZE THE SCRAMJET INLET DESIGN APPLYING THE TOTAL PRESSURE RECOVERYapplication/pdf1747510https://repositorio.ufrn.br/bitstream/123456789/43011/3/TCC_Alef.pdfa2525e960ea4080f2f7b718617b51840MD53LICENSElicense.txttext/plain762https://repositorio.ufrn.br/bitstream/123456789/43011/4/license.txte428689918449bd69f843393981e4109MD54123456789/430112023-03-05 10:21:18.289oai:https://repositorio.ufrn.br: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ório de PublicaçõesPUBhttp://repositorio.ufrn.br/oai/opendoar:2023-03-05T13:21:18Repositório Institucional da UFRN - Universidade Federal do Rio Grande do Norte (UFRN)false
dc.title.pt_BR.fl_str_mv A new approach to optimize the scramjet inlet design applying the total pressure recovery
title A new approach to optimize the scramjet inlet design applying the total pressure recovery
spellingShingle A new approach to optimize the scramjet inlet design applying the total pressure recovery
Fernandes, Alef Giovane Lima do Nascimento
Engenharia Mecânica. Fenômenos de Transporte. Mecânica dos Fluidos.
Scramjet. Supersonic combustion ramjet. Hypersonic airbreathing propulsion.
title_short A new approach to optimize the scramjet inlet design applying the total pressure recovery
title_full A new approach to optimize the scramjet inlet design applying the total pressure recovery
title_fullStr A new approach to optimize the scramjet inlet design applying the total pressure recovery
title_full_unstemmed A new approach to optimize the scramjet inlet design applying the total pressure recovery
title_sort A new approach to optimize the scramjet inlet design applying the total pressure recovery
author Fernandes, Alef Giovane Lima do Nascimento
author_facet Fernandes, Alef Giovane Lima do Nascimento
author_role author
dc.contributor.referees1.none.fl_str_mv Borba, Gilvan Luiz
dc.contributor.referees2.none.fl_str_mv Bessa, Kleiber Lima de
dc.contributor.author.fl_str_mv Fernandes, Alef Giovane Lima do Nascimento
dc.contributor.advisor1.fl_str_mv Marinho, George Santos
contributor_str_mv Marinho, George Santos
dc.subject.cnpq.fl_str_mv Engenharia Mecânica. Fenômenos de Transporte. Mecânica dos Fluidos.
topic Engenharia Mecânica. Fenômenos de Transporte. Mecânica dos Fluidos.
Scramjet. Supersonic combustion ramjet. Hypersonic airbreathing propulsion.
dc.subject.por.fl_str_mv Scramjet. Supersonic combustion ramjet. Hypersonic airbreathing propulsion.
description CNPq
publishDate 2019
dc.date.accessioned.fl_str_mv 2019-12-10T14:03:09Z
2021-10-05T15:59:45Z
dc.date.available.fl_str_mv 2019-12-10T14:03:09Z
2021-10-05T15:59:45Z
dc.date.issued.fl_str_mv 2019-12-05
dc.type.status.fl_str_mv info:eu-repo/semantics/publishedVersion
dc.type.driver.fl_str_mv info:eu-repo/semantics/bachelorThesis
format bachelorThesis
status_str publishedVersion
dc.identifier.pt_BR.fl_str_mv 20180154459
dc.identifier.citation.fl_str_mv FERNANDES, Alef Giovane Lima do Nascimento. A new approach to optimize the scramjet inlet design applying the total pressure recovery. 2019. 9 f. Trabalho de Conclusão de Curso (Graduação em Engenharia Mecânica) - Centro de Tecnologia, Departamento de Engenharia Mecânica, Universidade Federal do Rio Grande do Norte, Natal, 2019.
dc.identifier.uri.fl_str_mv https://repositorio.ufrn.br/handle/123456789/43011
identifier_str_mv 20180154459
FERNANDES, Alef Giovane Lima do Nascimento. A new approach to optimize the scramjet inlet design applying the total pressure recovery. 2019. 9 f. Trabalho de Conclusão de Curso (Graduação em Engenharia Mecânica) - Centro de Tecnologia, Departamento de Engenharia Mecânica, Universidade Federal do Rio Grande do Norte, Natal, 2019.
url https://repositorio.ufrn.br/handle/123456789/43011
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 Universidade Federal do Rio Grande do Norte
dc.publisher.initials.fl_str_mv UFRN
dc.publisher.country.fl_str_mv Brasil
dc.publisher.department.fl_str_mv Engenharia Mecânica
publisher.none.fl_str_mv Universidade Federal do Rio Grande do Norte
dc.source.none.fl_str_mv reponame:Repositório Institucional da UFRN
instname:Universidade Federal do Rio Grande do Norte (UFRN)
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