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dc.contributor.authorScalabrin, Leonardo Costapt_BR
dc.contributor.authorAzevedo, João Luiz Filgueiras dept_BR
dc.contributor.authorTeixeira, Paulo Roberto de Freitaspt_BR
dc.contributor.authorAwruch, Armando Miguelpt_BR
dc.date.accessioned2013-07-11T02:22:00Zpt_BR
dc.date.issued2004pt_BR
dc.identifier.issn1678-5878pt_BR
dc.identifier.urihttp://hdl.handle.net/10183/75780pt_BR
dc.description.abstractAerodynamic flow simulations over the first Brazilian satellite launch vehicle, VLS, during its first-stage flight are presented. The three dimensional compressible flow is modeled by the Euler equations and a Taylor-Galerkin finite element method with artificial dissipation is used to obtain the numerical solution. Transonic and supersonic results for zero angleof- attack are presented and compared to available experimental results. The influence of mesh refinement and artificial dissipation coeffcient on the transonic flow results are discussed. The results obtained for the supersonic simulations present good agreement with experimental data. The transonic simulation results capture the correct trends but they also indicate that this flight condition requires more refined meshes.en
dc.format.mimetypeapplication/pdf
dc.language.isoengpt_BR
dc.relation.ispartofJournal of the Brazilian Society of Mechanical Sciences and Engineering. Rio de Janeiro, RJ. Vol. 26, no. 2 (Apr./June 2004), p. 107-116pt_BR
dc.rightsOpen Accessen
dc.subjectAeronautical engineeringen
dc.subjectFluidos compressíveispt_BR
dc.subjectSimulação numéricapt_BR
dc.subjectComputational fluid dynamicsen
dc.subjectMecânica dos fluidospt_BR
dc.subjectFinite element techniqueen
dc.subjectTaylor-Galerkin methoden
dc.subjectTransonic flowsen
dc.subjectSupersonic flowsen
dc.titleThree dimensional flow simulations with the finite element technique over a multi-stage rocketpt_BR
dc.typeArtigo de periódicopt_BR
dc.identifier.nrb000432209pt_BR
dc.type.originNacionalpt_BR


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