Simulação numérica da interação entre uma nuvem incidente de vórtices e uma aerofólio através do método dos vórtices

The study of aerodynamic loading variations has many engineering applications, including helicopter rotor blades, wind turbines and turbo machinery. This work uses a Vortex Method to make a lagrangian description of the a twodimensional airfoil/ incident wake vortex interaction. The flow is incompressible, newtonian, homogeneus and the Reynolds Number is 5x105 .The airfoil is a NACA 0018 placed a angle of attack of the 0° and 5°simulates with the Painel Method with a constant density vorticity panels and a generation poit is near the painel. The protector layer is created does not permit vortex inside the body. The vortex Lamb convection is realized with the Euler Method (first order) and Adans-Bashforth (second order). The Random Walk Method is used to simulate the diffusion. The circular wake has 366 vortex all over positive or negative vorticity located at different heights with respect to the airfoil chord. The Lift was calculated based in the algorithm created by Ricci (2002). This simulation uses a ready algorithm vatidated with single body does not have a incident wake. The results are compared with a experimental work The comparasion concludes that the experimental results has a good agrement with this papper

Controle da variação do arqueamento de um aerofólio utilizando atuadores de memória de forma

Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES)

Concepção, modelagem, simulação e usinagem de um aerofólio automotivo auxiliado por computador

With the advancement of computer technology and the availability of technology computer aided design (CAD) errors in the designs are getting smaller. To this end the project aims to assess the reliability of the machine (CNC), which was designed by students of mechanical engineering college engineering - UNESP Bauru, by designing, modeling, simulation and machining an airfoil automotive. The profile template selected for the study will be a NACA 0012 machined plates in medium density fiberboard (MDF) and will be performed with a structural analysis simulation using finite elements and a software CFD (Computational Fluid Dynamics), and test the real scale model in a wind tunnel. The results obtained in the wind tunnel and CFD software will be compared to see the error in the machining process.

Otimização de geometrias aerodinâmicas utilizando métodos inversos

O objetivo deste trabalho é a obtenção de uma técnica para a modelagem otimizada de corpos submetidos a fluxos de alta velocidade, como aerofólios em escoamentos transônicos e outras geometrias aerodinâmicas. A técnica é desenvolvida através de expansões em séries de Fourier para um conjunto de equações diferenciais com interrelação com as condições de contorno, sendo uma equação para a parte superior e outra para a parte inferior do aerofólio. O método de integração temporal empregado baseia-se no esquema explícito de Runge-Kutta de 5 estágios para as equações da quantidade de movimento e na relação de estado para a pressão. Para a aproximação espacial adota-se um esquema em volumes finitos no arranjo co-localizado em diferenças centrais. Utiliza-se dissipação artificial para amortecer as frequências de alta ordem do erro na solução das equações linearizadas. A obra apresenta a solução de escoamentos bi e tridimensionais de fluidos compressíveis transônicos em torno de perfis aerodinâmicos. Os testes num´ericos são realizados para as geometrias do NACA 0012 e 0009 e asas tridimensionais usando as equações de Euler, para número de Mach igual a 0.8 e ® = 0o. Os resultados encontrados comparam favoravelmente com os dados experimentais e numéricos disponíveis na literatura.

Análise aerodinâmica de perfis de asa para aeronaves experimentais tipo jn-1

The great importance in selecting the profile of an aircraft wing concerns the fact that its relevance in the performance thereof; influencing this displacement costs (fuel consumption, flight level, for example), the conditions of flight safety (response in critical condition) of the plane. The aim of this study was to examine the aerodynamic parameters that affect some types of wing profile, based on wind tunnel testing, to determine the aerodynamic efficiency of each one of them. We compared three types of planforms, chosen from considerations about the characteristics of the aircraft model. One of them has a common setup, and very common in laboratory classes to be a sort of standard aerodynamic, it is a symmetrical profile. The second profile shows a conFiguration of the concave-convex type, the third is also a concave-convex profile, but with different implementation of the second, and finally, the fourth airfoil profile has a plano-convex. Thus, three different categories are covered in profile, showing the main points of relevance to their employment. To perform the experiment used a wind tunnel-type open circuit, where we analyzed the pressure distribution across the surface of each profile. Possession of the drag polar of each wing profile can be, from the theoretical basis of this work, the aerodynamic characteristics relate to the expected performance of the experimental aircraft, thus creating a selection model with guaranteed performance aerodynamics. It is believed that the philosophy used in this dissertation research validates the results, resulting in an experimental alternative for reliable implementation of aerodynamic testing in models of planforms

Controle nebuloso aplicado em asas adaptativas utilizando ligas de memória de forma

Pós-graduação em Engenharia Mecânica - FEIS

Projeto de controladores robustos para aplicações em estruturas inteligentes utilizando desigualdades matriciais lineares

Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES)

Estudo da formação de gelo não detectável em aeronaves de transporte

Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES)