This thesis deals with Computational Fluid Dynamics (CFD)simulations of the flow around delta wings at high angles ofattack. These triangular wings, mainly used in militaryaircraft designs, experience the formation of two vortices ontheir lee-side at large angles of attack. The simulation ofthis vortical flow by solving the Navier-Stokes equations isthe subject of this thesis. The purpose of the work is toimprove the understanding of this flow and contribute to thedesign of such a wing by developing methods that enable moreaccurate and efficient CFD simulations. Simulations of the formation, burst and disappearance of thevortices while the angle of attack is changing are presented.The structured flow solver NSMB has been used to get thetime-dependent solutions of the flow. Both viscous and inviscidresults of a 70°-swept delta wing pitching in anoscillatory motion are reported. The creation of the dynamiclift and the hysteresis observed in the history of theaerodynamic forces are well reproduced. The second part of the thesis is focusing on automatic meshrefinement and its influence on simulations of the delta wingleading-edge vortices. All the simulations to assess the gridquality are inviscid computations performed with theunstructured flow solver EDGE. A first study reports on theeffects of refining thewake of the delta wing. A70°-swept delta wing at a Mach number of 0.2 and an angleof attack of 27° where vortex breakdown is present abovethe wing, is used as testcase. The results show a strongdependence on the refinement, particularly the vortex breakdownposition, which leads to the conclusion that the wake should berefined at least partly. Using this information, a grid for thewing in the wind tunnel is created in order to assess theinfluence of the tunnel walls. Three sensors for automatic meshrefinement of vortical flows are presented. Two are based onflow variables (production of entropy and ratio of totalpressures) while the third one requires an eigenvalue analysisof the tensor of the velocity gradients in order to capture theposition of the vortices in the flow. These three vortexsensors are successfully used for the simulation of the same70° delta wing at an angle of attack of 20°. Acomparison of the sensors reveals the more local property ofthe third one based on the eigenvalue analysis. This lattertechnique is applied to the simulation of the wake of a deltawing at an angle of attack of 20°. The simulations on ahighly refined mesh show that the vortex sheet shed from thetrailing-edge rolls up into a vortex that interacts with theleading-edge vortex. Finally the vortex-detection technique isused to refine the grid around a Saab Aerosystems UnmannedCombat Air Vehicle (UCAV) configuration and its flight dynamicscharacteristics are investigated. Key words:delta wing, high angle of attack, vortex,pitching, mesh refinement, UCAV, vortex sensor, tensor ofvelocity gradients.

<p>This thesis deals with Computational Fluid Dynamics (CFD)simulations of the flow around delta wings at high angles ofattack. These triangular wings, mainly used in militaryaircraft designs, experience the formation of two vortices ontheir lee-side at large angles of attack. The simulation ofthis vortical flow by solving the Navier-Stokes equations isthe subject of this thesis. The purpose of the work is toimprove the understanding of this flow and contribute to thedesign of such a wing by developing methods that enable moreaccurate and efficient CFD simulations.</p><p>Simulations of the formation, burst and disappearance of thevortices while the angle of attack is changing are presented.The structured flow solver NSMB has been used to get thetime-dependent solutions of the flow. Both viscous and inviscidresults of a 70°-swept delta wing pitching in anoscillatory motion are reported. The creation of the dynamiclift and the hysteresis observed in the history of theaerodynamic forces are well reproduced.</p><p>The second part of the thesis is focusing on automatic meshrefinement and its influence on simulations of the delta wingleading-edge vortices. All the simulations to assess the gridquality are inviscid computations performed with theunstructured flow solver EDGE. A first study reports on theeffects of refining thewake of the delta wing. A70°-swept delta wing at a Mach number of 0.2 and an angleof attack of 27° where vortex breakdown is present abovethe wing, is used as testcase. The results show a strongdependence on the refinement, particularly the vortex breakdownposition, which leads to the conclusion that the wake should berefined at least partly. Using this information, a grid for thewing in the wind tunnel is created in order to assess theinfluence of the tunnel walls. Three sensors for automatic meshrefinement of vortical flows are presented. Two are based onflow variables (production of entropy and ratio of totalpressures) while the third one requires an eigenvalue analysisof the tensor of the velocity gradients in order to capture theposition of the vortices in the flow. These three vortexsensors are successfully used for the simulation of the same70° delta wing at an angle of attack of 20°. Acomparison of the sensors reveals the more local property ofthe third one based on the eigenvalue analysis. This lattertechnique is applied to the simulation of the wake of a deltawing at an angle of attack of 20°. The simulations on ahighly refined mesh show that the vortex sheet shed from thetrailing-edge rolls up into a vortex that interacts with theleading-edge vortex. Finally the vortex-detection technique isused to refine the grid around a Saab Aerosystems UnmannedCombat Air Vehicle (UCAV) configuration and its flight dynamicscharacteristics are investigated.</p><p><b>Key words:</b>delta wing, high angle of attack, vortex,pitching, mesh refinement, UCAV, vortex sensor, tensor ofvelocity gradients.</p>

Orientadores: Antonio Augusto Fasolo Quevedo, Waldir Antonio Bizzo / Dissertação (mestrado) - Universidade Estadual de Campinas, Faculdade de Engenharia Eletrica e de Computação / Made available in DSpace on 2018-08-14T20:06:15Z (GMT). No. of bitstreams: 1 Ramos_AndredePaula_M.pdf: 3634888 bytes, checksum: 6ac215157ad6cab344d793b24a2bc1cd (MD5) Previous issue date: 2009 / Resumo: O espirômetro é um dispositivo que avalia a ventilação pulmonar. Este é um trabalho preliminar que propõe um sensor eletromecânico de fluxo com foco na aplicação biomédica de espirometria. O sensor consiste de um corpo rombudo, introduzido em um cano por um orifício, e um acelerômetro. A colisão das partículas do fluido contra o corpo rombudo gera vórtices, que por sua vez induzem vibrações no corpo. Forças de arrasto também estão presentes e tendem a movimentar o corpo. Os movimentos decorrentes do escoamento são captados pelo acelerômetro, que é posicionado na porção do corpo rombudo externa ao cano, evitando o contato do elemento eletrônico (acelerômetro) com o fluido, o que pode facilitar procedimentos de esterilização da luz do cano. Foram analisados corpos rombudos em forma de lâmina (com e sem massa adicional) e cilindro. O procedimento experimental consistiu no estabelecimento de seis regimes permanentes de entrada (vazão de ar) e na captura do sinal de resposta do sensor (nos três eixos). Foram coletadas 24 respostas do sensor para cada um dos regimes e posteriormente foram levantadas as curvas do sensor e realizadas análises estatísticas. Resultados significativos foram encontrados para o eixo do acelerômetro paralelo ao fluxo. Para a lâmina, o Valor Eficaz (RMS) do sinal foi proporcional à vazão com linearidade e coeficiente de correlação variando, respectivamente, de 19% e R2 = 0,99058, para o ensaio sem massa adicional, a até 8,4% e R2 = 0,9741, para o ensaio com massa adicional. O arrasto contínuo (valor médio da resposta) não guardou relação monotônica com o aumento da velocidade do ar. Já para o cilindro, o arrasto foi proporcional à vazão com altíssima linearidade e correlação (0,17% e R2 = 0,96347), mas o RMS do sinal não guardou relação monotônica com a vazão. Finalmente, embora sejam necessários mais estudos para utilizar o sensor proposto em equipamentos de espirometria, este trabalho demonstra que o sensor responde proporcionalmente às entradas (escoamento), dentro (de 0 a até 14 l/s) e fora da faixa (até 21 l/s) de operação do espirômetro com altos coeficientes de correlação e linearidade, além de respostas diferenciadas dadas diferentes entradas (vazões) comprovadas por ANOVA (valor de p < 10-15). / Abstract Spirometer is a device that evaluates pulmonary ventilation. This paper presents a preliminary study of a new electromechanical sensor, focused on the biomedical application of spirometry. The sensor is composed of a bluff body positioned inside a tube trough a hole, being a part of the body inside and another part outside of the tube, and an accelerometer positioned on the outside part. Within a fluid flow, the bluff body causes vortex shedding, and the vortexes induce vibrations on the body. Also, the viscous force of the flow drags the bluff body. Both movements are captured by the accelerometer and correlated with the flow. One important feature of this sensor is that the fluid does not contact any of the electronics, easing tube lumen sterilization procedures. Three types of bluff bodies were studied: two blades (with and without additional mass), and one cylinder. The experimental procedure consisted of establishing six different air flows and then capturing the accelerometer response in all of its three axes. Each of the collected signals from the accelerometer was divided in 24 parts, and these parts where analyzed through statistics; finally the mean response of the sensor was plotted. Best results were found in the accelerometer axis parallel to the air flow. In the blade tests, the RMS value of the AC component was proportional to the air flow, with linearity and correlation varying, respectively, from 19% and R2 = 0.99058 for the blade without mass, to 8.4% and R2 = 0.9741 for the blade with additional mass. It was observed that the mass addition reduced in a meaningful way the response variances. Yet the viscous force (DC value) did not respond in a monotonic way with the increase of air flow. On the other hand, the viscous force was the most expressive regarding the experiments with the cylinder (linearity of 0.17% and R2 = 0.96347), but the RMS value did not respond in a monotonic way. Finally, although further studies are needed to prove that the proposed sensor is efficient to be used in spirometry equipment, this study demonstrates that this sensor responds proportionally to the flow input, within (0 to 14 l/s) and without (up to 21 l/s) the spirometer operation range, with high correlation and linearity, as well as varying responses, given different inputs (flow), as verified by ANOVA test (p < 10-15). / Mestrado / Engenharia Biomedica / Mestre em Engenharia Elétrica