Análise Numérica e Experimental da Influência de Dispositivos de Ponta de Asa no Perfil Aerodinâmico NACA 23015

• Autor(a) principal: Magro, Diogenes Dal
• Data de Publicação: 2020
• Outros Autores: Neumeister, Roberta
• Tipo de documento: Artigo
• Idioma: por
• Título da fonte: Revista Interdisciplinar de Pesquisa em Engenharia
• Texto Completo: https://periodicos.unb.br/index.php/ripe/article/view/29702
• topic: Winglets. Pressure distribution. Drag Coefficient. Lift Coefficient.; Dispositivo de ponta de asa; Distribuição de pressão; Coeficiente de arrasto; Coeficiente de sustentação.

Agricultural aviation has peculiar operating characteristic as the low flight altitudes and the need for precise maneuvers in a short time, these aircraft demand high aerodynamic efficiency. An alternative to improve the performance of these aircraft is the use of a wingtip device. The present work presents a numerical-experimental analysis about the influence of the use of wing tip devices in an aerodynamic profile NACA 23015. The analyzes were performed using two angles of attack. The first was 6 °, as the angle of installation of the wing in an aircraft is commonly and the second was 15 °, a value close to the stall angle. The experimental analyzes were performed in an open circuit aerodynamic channel. Numerical analyzes were performed using the Reynolds-Averaged Navier-Stokes (RANS) equations using the k-ω SST turbulence model. The results obtained by the numerical and experimental methods showed similar values, with only differences in the region of minimum pressure being observed. With the addition of the wing tip device, it was possible to observe an increase of approximately 5.5% and 3.0% in aerodynamic efficiency with angles of attack of 6 and 15 degrees respectively, both in numerical analysis and in experimental tests. Therefore, it is possible to conclude that the device developed in this work can be used as an alternative to optimize the aerodynamic performance of aircraft.