The later stages of separated shear layer transition within separation bubbles developing over a NACA0018 airfoil operating at a chord Reynolds number of 105 and at angles of attack of 0, 5, 8, and 10 degrees were investigated experimentally in a wind tunnel. Several experimental tools, including a rake of six boundary-layer hot-wire anemometers, were used to perform measurements over the model. Novel high-speed flow visualization performed with a smoke-wire placed within the separated shear layer showed that roll-up vortices are shed within separation bubbles forming on the suction side of the airfoil. The structures were found to convect downstream and eventually break down during laminar-to-turbulent transition. Top view visualizations revealed that, at angles of attack of 0, 5, and 8 degrees, roll-up vortices form coherently across the span and undergo significant spanwise deformations prior to breaking down. At angles of attack of 5 and 8 degrees, rows of streamwise-oriented structures were observed to form during vortex breakdown. Statistics regarding the formation and development of shear layer roll-up vortices were extracted from high-speed flow visualization sequences and compared to the results of boundary layer measurements. It was found that, on the average, roll-up vortices form following the initial exponential growth of unstable disturbances within the separated shear layer and initiate the later stages of transition. The onset of these nonlinear stages was found to occur when the amplitude of velocity disturbances reached approximately 10% of the free-stream velocity. The rate of vortex shedding was found to fall within the frequency band of the unstable disturbances and lie near the central frequency of this band. The formation of vortices has been linked to the generation of harmonics of these unstable disturbances in velocity signals acquired ahead of mean transition. Once shed, vortices were found to drift at speeds between 33% and 44% of the edge velocity. Vortex merging at an angle of attack of 5?? was investigated. It was found that the majority of roll-up vortices proceed to merge with either one or two other vortices. Vortex merging between two and three vortices was found to occur periodically in a process similar to vortex merging in plane mixing layers undergoing subharmonic forcing of the most amplified disturbance. The flapping motion of the separated shear layer was investigated by performing a cross-correlation analysis on the high-speed flow visualization sequences to extract vertical displacement signals of the smoke within the shear layer. The frequency of flapping was found to correspond to the unstable disturbance band. At an angle of attack of 5??, it was found that the separated shear layer has a low-frequency component of flapping that matches a strong peak in velocity and surface pressure spectra that lies outside the unstable disturbance frequency band. The spanwise development of disturbances was assessed in the aft portion of the separation bubbles by performing a cross-correlation analysis on signals acquired simultaneously across the span with the rake of hot-wires. The spanwise correlations between signals was found to be well-correlated ahead of shear layer roll-up, after which disturbances became rapidly uncorrelated ahead of mean reattachment. These results were found to be linked to the coherent roll-up and subsequent breakdown of roll-up vortices.

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[pt] O presente trabalho consiste no projeto, construção e qualificação de um aparato para o estudo experimental de bolhas de separação laminar sobre uma placa plana. A previsão do comportamento das bolhas de separação é importante para o projeto de aeronaves, turbinas e geradores eólicos, pois o desprendimento dessas bolhas tem grande impacto na performance de aerofólios. A dinâmica das bolhas não é bem compreendida, além de ser difícil de ser capturada por simulações numéricas que utilizam modelagem da turbulência. Por isso, ensaios experimentais são muito utilizados para a calibração dos modelos utilizados em simulações de engenharia. Neste trabalho, foram criados equipamentos para simular experimentalmente bolhas de separação laminar sobre uma placa plana. Os dispositivos foram projetados para o canal de água do Laboratório de Engenharia de Fluidos da PUC-Rio. O gradiente de pressão necessário para induzir a separação da camada limite e consequente formação da bolha foi ajustado com uma parede falsa, de modo a criar um canal convergente-divergente com a placa plana. Foi projetado um mecanismo de sucção da camada limite na parede falsa para evitar a separação do escoamento nessa superfície. A localização e as vazões de cada ponto de sução foram determinadas com o auxílio de simulações numéricas. Também foi projetado e testado um sistema de sopro e sucção para a excitação de ondas de instabilidade do tipo Tollmien-Schlichting na camada limite da placa plana. O funcionamento de cada dispositivo foi avaliado através da medição da velocidade do escoamento. Para isso, foram empregadas técnicas de medição por velocimetría laser doppler e velocimetría por imagem de partículas. Os resultados obtidos validam o projeto e qualificam o aparato para o estudo de bolhas de separação laminar. / [en] The present work involves the design, construction and performance test of an apparatus for the investigation of laminar separation bubbles in a flat plate boundary layer. Laminar separation bubbles are relevant for many engineering applications and the dynamic of such bubbles has a strong impact on the performance of aircrafts and turbines. The separated boundary layer reattaches to the surface due to the laminar-turbulent transition in the bubble region. This dynamic process is highly challenging for flow simulation tools used for engineering purposes. Thus, there is a demand for experimental studies that can be used for calibration of models present in those simulation tools. To this end, an apparatus was designed and built for the water channel of the Laboratory of Fluid Engineering at PUC-Rio. The boundary layer separation on the flat plate was induced by imposing a constant adverse pressure gradient to the flow. To this end a false wall was built, in order to form a converging-diverging channel with the flat plate. Flow separation on the false wall was avoided using a suction mechanism that was designed to reduce locally the boundary layer thickness. Location of suction and suction flow rates were determined with aid of numerical simulations. In addition, it was designed and built a disturbance source to generate Tollmien-Schlichting waves in the boundary layer of the flat plate. This device was used to trigger the boundary layer transition in a controlled manner. All equipment were tested and their designs were validated against experimental measurements. Laser Doppler anemometry and Particle Image Velocimetry techniques were adopted for assessment of each equipment. Results validate the design and show that separation bubbles can be investigated in detail using this apparatus.

[pt] O estudo de bolhas de separação laminar em aerofólios que operam a baixos números de Reynolds é importante para diversas aplicações tais como: turbinas a gás, geradores eólicos, veículos aéreos não tripulados, dentre outros. A perda de performance desses equipamentos, normalmente, está associada à presença e à ruptura de bolhas de separação. Neste trabalho buscou-se investigar, experimentalmente, os efeitos relacionados a variação súbita no nível de perturbações do escoamento a montante da região de formação da bolha. A ideia é avaliar como o escoamento se comporta em uma situação onde o nível de turbulência do escoamento livre pode variar. No caso de turbinas, essa condição pode ser observada quando as esteiras dos aerofólios de um estágio influenciam aquelas do estágio seguinte. Apesar da relevância prática, o regime transiente foi pouco investigado na literatura. Para o presente estudo foi utilizado um canal de água do Laboratório de Engenharia de Fluidos. O gradiente de pressão, necessário para a formação da bolha, foi gerado com uma placa convergente-divergente e o nível de perturbações na camada limite foi controlado através de um gerador do tipo fita vibrante. Os campos de velocidades na região da bolha foram medidos com a técnica de Velocimetria por Imagem de Partícula com alta resolução temporal. A geração de perturbações e as medições de velocidade foram sincronizadas, permitindo assim o uso de técnicas de extração de médias de eventos. Caracterizou-se a bolha em um regime estacionário, onde não houve excitação de perturbações controladas a montante da bolha. Os resultados foram comparados com referências da literatura, apresentando boa concordância. No regime transiente, analisou-se o escoamento desde o instante em que o gerador de perturbações foi subitamente desligado até a recuperação completa da bolha. Nessas condições, notou-se que bolha cresceu até atingir um comprimento maior do que o observado no regime estacionário. Somente após o desprendimento de um grande vórtice, a bolha voltou a exibir características similares àquelas do regime estacionário. Esse comportamento se assemelha àquele reportado na literatura para ruptura de bolhas (bursting) mas que ainda não é bem compreendido. / [en] Laminar separation bubbles in Low Reynolds number airfoils is important for several applications such as: gas turbines, wind generators, unmanned aerial vehicles, among others. The performance loss of this airfoils is usually associated with the presence and rupture of separation bubbles. The effects related to the sudden variation of the level of flow disturbances upstream of the bubble formation region are investigated in this work. The idea is to evaluate how the flow behaves when subjected to a sudden variation in the freestream turbulence. This condition can be observed in airfoil cascade of turbines, where the wake of a previous stage can influence the next. Although this scenario is of practical relevance, it has been poorly investigated in literature. For the present study, a water channel from the Fluids Engineering Laboratory was used. The pressure gradient, necessary for the bubble formation, was generated with a convergentdivergent plate and the level of disturbances in the boundary layer was controlled using a vibrating ribbon. Velocity fields in the bubble region were measured using the Particle Image Velocimetry technique with high temporal resolution. The generation of disturbances and measurements were phase locked, thus allowing the use of ensemble average techniques. The bubble was characterized in a so called steady regime, where there was no excitation of controlled disturbances upstream of the bubble. The results were compared with references in the literature, showing good agreement. In the transient regime, the flow was analyzed from the moment the disturbance generator was suddenly turned off until the bubble had completely recovered. In these conditions, it was noted that the bubble grew until reaching a length greater than that observed in the stationary regime. Only after the release of a large vortex did the bubble return to exhibit characteristics similar to those of the stationary regime. This behavior is similar to that reported in the literature for bubble rupture (bursting) but that is still not well understood.