1. Repositório Institucional - Universidade Federal de Uberlândia
  2. Faculdade de Engenharia Mecânica (FEMEC)
  3. TCC - Engenharia Aeronáutica
Please use this identifier to cite or link to this item: https://repositorio.ufu.br/handle/123456789/43783
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dc.creatorCastro, Thiago Rezende de-
dc.date.accessioned2024-11-04T18:05:26Z-
dc.date.available2024-11-04T18:05:26Z-
dc.date.issued2024-08-16-
dc.identifier.citationCASTRO, Thiago Rezende de. Numerical Simulations of High-lift Configurations on a NACA4412 Airfoil. 2024. 63 f. Trabalho de Conclusão de Curso (Graduação em Engenharia Aeronáutica) – Universidade Federal de Uberlândia, Uberlândia, 2024.pt_BR
dc.identifier.urihttps://repositorio.ufu.br/handle/123456789/43783-
dc.languageengpt_BR
dc.publisherUniversidade Federal de Uberlândiapt_BR
dc.rightsAcesso Abertopt_BR
dc.rights.urihttp://creativecommons.org/licenses/by-nc-nd/3.0/us/*
dc.subjectNumerical simulation; OpenFOAM; High-lift devices; Flaps.pt_BR
dc.titleNumerical Simulations of High-lift Configurations on a NACA4412 Airfoilpt_BR
dc.typeTrabalho de Conclusão de Cursopt_BR
dc.contributor.advisor1Almeida, Odenir de-
dc.contributor.advisor1Latteshttp://lattes.cnpq.br/8197975215358295pt_BR
dc.contributor.referee1Alemida, Odenir de-
dc.contributor.referee1Latteshttp://lattes.cnpq.br/8197975215358295pt_BR
dc.contributor.referee2Andrade, João Rodrigo-
dc.contributor.referee2Latteshttp://lattes.cnpq.br/3633955382225394pt_BR
dc.contributor.referee3Miranda, Luiz Paulo Borges-
dc.creator.Latteshttp://lattes.cnpq.br/1873963809945246pt_BR
dc.description.degreenameTrabalho de Conclusão de Curso (Graduação)pt_BR
dc.description.resumoThis work addresses the numerical simulation of high-lift systems in the aeronautical industry. The main objective was to evaluate the performance of different configurations of such high-lift devices, identifying their advantages and disadvantages. The secondary objective was to develop a robust numerical method for simulating flows around airfoils, using the OpenFOAM software. Numerical analyses were carried out on five different configurations — namely, the plain flap, split flap, slotted flap, Fowler flap and Junkers flap — under similar conditions, allowing for a consistent comparison of outcomes. All flaps were deflected by 10◦ and analyzed at a Reynolds of 1.7 · 105 over a range of angles of attack between −4 ◦ and 16◦ . The Spallart-Almarras turbulence model was used in all simulations, which were carried out in the steady state. Quantitative results were analyzed for the coefficients of lift (Cl ) and drag (Cd ) per unit length and the coefficient of pressure (Cp) on the surfaces of the airfoils analyzed, as well as the velocity and pressure fields of the flows. To check the quality of the simulation, the method was used to replicate experimental and numerical results obtained by other authors for the flow around airfoils (flapped or not). In addition, the convergence of the simulation between successively refined meshes and the quality of the boundary layer modeling from the dimensionless parameter y + were analyzed, and both obtained good results with residual errors in the order of 10−5 . The results obtained show the efficiency and robustness of the proposed method and its applicability in different scenarios. It was found that the simulations presented reliable and coherent results for lift and drag generation, but for angles of attack close to stall, convergence was more difficult. In addition, it was possible to identify the superiority in lift generation of the flap configurations most commonly used in the aeronautical industry, such as the slotted flap and the Fowler flap.pt_BR
dc.publisher.countryBrasilpt_BR
dc.publisher.courseEngenharia Aeronáuticapt_BR
dc.sizeorduration63pt_BR
dc.subject.cnpqCNPQ::ENGENHARIAS::ENGENHARIA AEROESPACIAL::AERODINAMICApt_BR
dc.subject.cnpqCNPQ::ENGENHARIAS::ENGENHARIA AEROESPACIAL::SISTEMAS AEROESPACIAIS::AVIOESpt_BR
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