Análise numérica das características aerodinâmicas de uma asa de baixo alongamento com propulsão distribuída

Detalhes bibliográficos
Ano de defesa: 2020
Autor(a) principal: Rogério Rodrigues da Silva Filho
Orientador(a): Não Informado pela instituição
Banca de defesa: Não Informado pela instituição
Tipo de documento: Dissertação
Tipo de acesso: Acesso aberto
Idioma: por
Instituição de defesa: Universidade Federal de Minas Gerais
Brasil
ENG - DEPARTAMENTO DE ENGENHARIA MECÂNICA
Programa de Pós-Graduação em Engenharia Mecanica
UFMG
Programa de Pós-Graduação: Não Informado pela instituição
Departamento: Não Informado pela instituição
País: Não Informado pela instituição
Palavras-chave em Português:
Link de acesso: http://hdl.handle.net/1843/34929
https://orcid.org/0000-0001-5412-1308
Resumo: Distributed propulsion concept expands the boundaries of aircraft designs, therefore, the study of aerodynamic effects due to propulsion/wing interaction is extremely important for the elaboration of a wing as efficient as possible in the aerodynamic and structural scope. The objective of the present research is to analyze the effects of the distributed propulsion concept, in tractor configuration, on the flow field around a low-aspect-ratio wing and evaluating the changes in aerodynamic characteristics. Numerical methods based in Reynolds-Averaged Navier-Stokes equations were used, including the k-ω SST turbulence model and an actuator disk model based on blade element theory that represent the propulsion; when validated through experimental data found in literature, numerical methods showed good representation of the flow physics, especially in wing regions directly affected by the propulsion flow-field. Results demonstrate that the flow induced by the distributed propulsion significantly alters the flow field around the wing and consequently alters the aerodynamic characteristics of the wing. When comparing the distributed propulsion concept with a base wing without interaction effects, it was observed that: i) there was a displacement of the lift curve, changing the lift to a certain angle of attack; ii) the change in lift curve slope and iii) increase the maximum lift coefficient value. In addition, the combinations of the propeller rotation directions can considerably modify the pressure, lift and shear stress distributions on the wing that being able to change the regions where the flow begins to separate from the wing surface and changing the load distributions. When considered in a cruise flight, the wing showed an increase in the aerodynamic efficiency which indicates drag reduction due to propulsion/wing interaction.