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Propeller optimization approach: Blade Element Momentum Theory in accelerated differential evolution

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dc.contributor.advisor1Vedovotto, João Marcelo
dc.contributor.advisor1Latteshttp://lattes.cnpq.br/5630598971511798pt_BR
dc.contributor.referee1Vedovotto, João Marcelo
dc.contributor.referee1Latteshttp://lattes.cnpq.br/5630598971511798pt_BR
dc.contributor.referee2Cavallini Junior, Aldemir Aparecido
dc.contributor.referee2Latteshttp://lattes.cnpq.br/0387727577180664pt_BR
dc.contributor.referee3Elias, Alex José
dc.contributor.referee3Latteshttp://lattes.cnpq.br/6260628541386586pt_BR
dc.creatorNonaka, Iago Tetsuo
dc.date.accessioned2024-07-02T17:43:26Z
dc.date.available2024-07-02T17:43:26Z
dc.date.issued2023-12-01
dc.description.degreenameTrabalho de Conclusão de Curso (Graduação)pt_BR
dc.description.resumoAircraft engines operate by Newton's Third Law, which states that for every action, there is a reaction. Normally, those that operate at low Mach produce thrust by a combination of engine and propeller. The propeller works by pushing air backward, it may propel a high quantity of air at a lower speed until a small quantity at higher velocities. In this thesis, an analytical method to optimize the design and performance of a propeller is presented. The main objective is to create an approach, that defines an optimal airscrew that will best suit an engine. Accurate propeller predictions are crucial in aircraft performance since detailed analysis consists of computational simulations or experiments, which are highly time-consuming and expensive. First, the Blade Element Momentum Theory is implemented, based on a database built by XFOIL. To validate, the results are compared with other analytical and experimental results from other theses. Then, an algorithm of optimization called Accelerated Differential Evolution was implemented. It developed an optimized propeller that produces 4\% higher efficiency compared to the one made for an electrical aircraft.pt_BR
dc.identifier.citationNONAKA, Iago Tetsuo. Propeller optimization approach: Blade Element Momentum Theory in accelerated differential evolution. 2023. 58 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/123456789/41541
dc.languageengpt_BR
dc.orcid.putcode162863621
dc.publisherUniversidade Federal de Uberlândiapt_BR
dc.publisher.countryBrasilpt_BR
dc.publisher.courseEngenharia Aeronáuticapt_BR
dc.rightsAcesso Abertopt_BR
dc.rightsAttribution 3.0 United States*
dc.rights.urihttp://creativecommons.org/licenses/by/3.0/us/*
dc.sizeorduration58pt_BR
dc.subjectPropellerpt_BR
dc.subjectBladept_BR
dc.subjectThrustpt_BR
dc.subjectOptimizationpt_BR
dc.subject.cnpqCNPQ::ENGENHARIAS::ENGENHARIA AEROESPACIAL::PROPULSAO AEROESPACIAL::MAQUINAS DE FLUXOpt_BR
dc.titlePropeller optimization approach: Blade Element Momentum Theory in accelerated differential evolutionpt_BR
dc.typeTrabalho de Conclusão de Cursopt_BR
dspace.entity.typePublication

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Blade Element Momentum Theory in Accelerated Differential Evolution
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TCC - Engenharia Aeronáutica