AERODYNAMIC LOADS MEASUREMENT OF A SOUNDING ROCKET VEHICLE TESTED IN WIND TUNNEL

Registro completo de metadados
MetadadosDescriçãoIdioma
Autor(es): dc.contributorInst Aeronaut & Space-
Autor(es): dc.contributorUniversidade Estadual Paulista (Unesp)-
Autor(es): dc.creatorReis, Maria Luisa-
Autor(es): dc.creatorFalcao, Joao Batista-
Autor(es): dc.creatorPaulino, Giuliano [UNESP]-
Autor(es): dc.creatorTruyts, Claudio-
Autor(es): dc.creatorIMEKO-
Data de aceite: dc.date.accessioned2022-02-22T00:03:39Z-
Data de disponibilização: dc.date.available2022-02-22T00:03:39Z-
Data de envio: dc.date.issued2020-12-09-
Data de envio: dc.date.issued2020-12-09-
Data de envio: dc.date.issued2009-01-01-
Fonte completa do material: dc.identifierhttp://hdl.handle.net/11449/194713-
Fonte: dc.identifier.urihttp://educapes.capes.gov.br/handle/11449/194713-
Descrição: dc.descriptionIn wind tunnels, aerospace vehicle models are tested in order to analyze their performance in real flight situations. The forces and moments exerted by the airflow on the surface of the test article are measured using multicomponent balances. The balance measures the aerodynamic loads by using strain-gages. It is calibrated prior to the tests, resulting in the estimation of the parameters of the polynomial mathematical modelling relating the strain-gage readings to the aerodynamic loads. This paper presents the aerodynamic load values acting on a sounding rocket vehicle under test in a transonic aerodynamic facility. The force and moment coefficients and corresponding uncertainties are also estimated. The vehicle was tested in low Mach number conditions, with the airflow being supplied by the injection system. The second stage of the model was fitted with three different fin deflections. The measured quantities are total pressure, static pressure and total temperature of the flow, as well as the strain gage readings supplied by an internal balance. An analysis of the contribution for the uncertainties in the aerodynamic loads revealed that the measurement precision is the dominant component. The intermediate measurement-
Descrição: dc.descriptionConselho Nacional de Desenvolvimento Científico e Tecnológico (CNPq)-
Descrição: dc.descriptionInst Aeronaut & Space, Sao Jose Dos Campos, Brazil-
Descrição: dc.descriptionSao Paulo State Univ, Sao Carlos, SP, Brazil-
Descrição: dc.descriptionSao Paulo State Univ, Sao Carlos, SP, Brazil-
Descrição: dc.descriptionCNPq: 104775/2008-4-
Formato: dc.format1332-1337-
Idioma: dc.languageen-
Publicador: dc.publisherImeko-
Relação: dc.relationXix Imeko World Congress: Fundamental And Applied Metrology, Proceedings-
???dc.source???: dc.sourceWeb of Science-
Palavras-chave: dc.subjectmetrological reliability-
Palavras-chave: dc.subjectwind tunnel tests-
Palavras-chave: dc.subjectsounding rockets-
Título: dc.titleAERODYNAMIC LOADS MEASUREMENT OF A SOUNDING ROCKET VEHICLE TESTED IN WIND TUNNEL-
Aparece nas coleções:Repositório Institucional - Unesp

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