This thesis reports on investigations carried out to study of the effect of horizontal wall jets on rough, fixed and mobile beds in open channel flow. Experimental tests were carried out, using fixed and mobile sediment beds. Computer simulation models for the flow within the jet and resulting sediment transport were developed and their results analysed in this study. In the experimental phase, tests were carried out with both fixed and mobile sediment beds. The shape of the water surface, numerous point velocity measurements and measurements of the evolving scour hole shape were made. Detailed descriptions of the turbulent flow field over a fixed rough bed and for scour holes at equilibrium were obtained for a range of initial jet conditions. Fully turbulent, multiphase flow was modelled using the Fluent Computational Fluid Dynamics software. This was used to analyze the flow caused by a jet in a rectangle open-channel with a rough bed, and also the flow pattern in a channel with a local scour hole. The volume of fluid (VOF) multiphase method and K- model was used to model the fluid flow in both cases. The model predictions of velocity and shear stress were compared against experimental observations. The experimental data was used to develop new empirical relationships to describe the pattern of boundary shear stress caused by a wall jet over fixed beds and in equilibrium scour holes. These relationships were linked with existing bed-load transport rate models in order to predict the temporal evolution of scour holes. An analytical model describing the relationship between the wall jet flow and the development of a local scour hole shape was reported and its predictions compared with experimental data.

The focus of this thesis is to analyse the flight characteristics of the blended wingbody (BWB) unmanned aerial vehicle (UAV) Green Raven currently being developed by students at the Royal Institute of Technology (KTH) in Stockholm,Sweden. The purpose of evaluating a BWB aircraft is due to its potential increasein fuel efficiency and payload compared to conventional aircrafts which would enable more sustainable flights. The analysis is conducted in ANSYS Fluent 2020R2 where the goals are to extrapolate lift, drag and pitching moment coefficients,aerodynamic efficiency and evaluate stall patterns. The analysis is conducted with free stream velocities from 5 m/s to 40 m/s with5 m/s increments at angles of attack from −4◦ to stall plus 4◦. The result of thisthesis is that an analysis have not been able to be conducted due to a lack ofcomputational power. Thusly, the conclusion to this thesis is that to be able toperform a complete analysis of the Green Raven, a more powerful computer needsto be used.

During the production of steel in the LD converter the refractory lining is exposed to high temperature emulsion of steel, slag and gas. It protects the steel body of the vessel to come in contact with the molten steel.The main purpose of this work was to observe the temperature distribution profile in converter refractory lining which is very important to understand the life of the refractory lining of the LD converter.In this study, a three dimensional (3D) heat transfer model for the refractory lining of converter was developed. The lining of the refractory material was considered as magnesite brick for inner lining, dolomite for intermediate lining and steel shell as outer part. In order to do the numerical modeling, the CFD software Ansys Fluent 13.0 was used. After considering the proper dimensions, meshing, properties of the lining material and boundary conditions, the modeling in Ansys was performed in two stages. In the first stage, the modeling was performed by assuming that the converter is already heated and the inside temperature of the furnace is 1923K and the outside temperature of the steel body is 300K. In the second stage, the temperature change of the molten steel, slag and the gas was considered as function of blowing time and slag height based on theories from different references. Firstly, the three dimensional (3D) heat transfer model was used for the refractory lining of the converter to show transient heat flow through the lining at different times. Secondly, 3D modeling results from fluent 13.0 was used to develop temperature distribution profile through the lining at different height for different time steps and at different positions with time and also along the converter height from the bottom to top. It has been noticed that refractories in the lining in contact with steel and slag must be of good quality for the reduction of wear cost and downtime and therefore the reduction of refractory cost per ton of steel production.

When an aircraft is aerodynamically or structurally damaged in battle, it may not able to complete the mission and the damage may cause its loss. The subject of aircraft battle survivability is one of critical concern to many disciplines, whether military or civil. This thesis considered and focused on Computational Fluid Dynamics [CFD] predictions and experimental investigations into the effects of simulated battle damage on the low-speed aerodynamics of a fmite aspect ratio wing. Results showed that in two-dimensional [2d] and three-dimensional [3D] CFD simulations, Fluent's® models work reasonably well in predicting jets flow structures, pressure distributions, and pressure-coefficient Cp's contours but not for aerodynamic coefficients. The consequences were therefore that CFD prediction was poor on aerodynamic-coefficients increments. The prediction of Cp's achieved good agreement upstream and near the damage hole, but showed poor agreement at downstream of the hole. For the flow structure visualisation, at both weak and strong jet incidences, the solver always predicted pressure-distribution-coefficient lower at upstream and higher at downstream. The results showed relatively good agreement for the case of transitional and strong jet incidences but slightly poor for weak jet incidences. From the experimental results of Finite Wing, the increments for Aspect-ratio, AR6, AR8 and ARIO showed that as damage moves out towards the tip, aerodynamic-coefficients increments i.e. lift-loss and drag-rise decreased, and pitching-moment-coefficient increment indicated a more positive value at all incidence ranges and at all aspect ratios. Increasing the incidence resulted in greater magnitudes of lift-loss and drag-rise for all damage locations and aspect ratios. At the weak jet incidence 4° for AR8 and in all of the three damage locations, the main characteristics of the weak-jet were illustrated clearly. The increments were relatively small. Whilst at 8°, the flow structure was characterised as transitional to stronger-jet. In Finite Wing tests and for all damage locations, there was always a flow structure asymmetry. This was believed to be due to gravity, surface imperfection, and or genuine feature. An 'early strong jet' that indicated in Finite Wing-AR8 at 'transitional' incidence of 8°, also indicated in twodimensional results but at the weak-jet incidence of 4°. For the application of 2d data to AR6, AR8, and ARIO, an assessment of 2d force results led to the analysis that the tests in the AAE's Low Turbulence Tunnel for 2d were under-predicting the damage effects at low incidence, and over-predicting at high incidences. This suggested therefore that Irwin's 2d results could not be used immediately to predict three-dimensional.

To avoid the large amount of damage that floods can cause, spillway tunnels are used to control water levels. To ensure the safety of water transportation through spillway tunnels, the behaviour of the water throughout the tunnel is important to know. Physical experiments are time consuming and expensive, hence CFD simulations are a profitable option for investigating the performance of the spillway tunnel. In this project, simulations of water flow in a spillway tunnel were executed. A three dimensional model of the spillway tunnel in Zipingpu Water Conservancy Project was created in the software ANSYS Gambit. A coarse, middle and fine mesh with both hexahedral- and tetrahedral elements were also created for the model in ANSYS Gambit. The meshes were imported to ANSYS Fluent where the simulations, and a convergence analysis were made. The water flow was set to be described by the Reynolds-Averaged Navier-Stokes model, using the pressure solver, k-epsilon model and the VOF model. Physical experiments had previously been performed, and the simulated results were compared to these, in an attempt to find the parameters to replicate the experimental results to the greatest extent possible. The inlet velocity of the tunnel was known and the inlet boundary was set as a velocity inlet. The ceiling of the tunnel was set as a pressure inlet, the floor and walls were set as wall, and the outlet was set as pressure outlet. The simulated results showed similar behavior as the experimental results, but all differed from the experimental results. The grid convergence index, estimating the results' dependency on the mesh was 6.044 %. The flow was analyzed, and where the flow had unfavorable characteristics, such as a high cavitation number, the geometry of the spillway was altered in ANSYS Gambit to investigate if an improved geometry for the spillway tunnel could be found. The water flow in the revised geometry was simulated in ANSYS Fluent, and results showing flow with lower cavitation numbers was found.

Submitted by Cleide Dantas (cleidedantas@ufpa.br) on 2014-04-07T13:52:52Z No. of bitstreams: 2 license_rdf: 23898 bytes, checksum: e363e809996cf46ada20da1accfcd9c7 (MD5) Dissertacao_AnaliseComputacionalCampos.pdf: 8199135 bytes, checksum: 4e41ee450e20c1b754db24b43b82d5fa (MD5) / Approved for entry into archive by Ana Rosa Silva (arosa@ufpa.br) on 2014-06-16T13:18:05Z (GMT) No. of bitstreams: 2 license_rdf: 23898 bytes, checksum: e363e809996cf46ada20da1accfcd9c7 (MD5) Dissertacao_AnaliseComputacionalCampos.pdf: 8199135 bytes, checksum: 4e41ee450e20c1b754db24b43b82d5fa (MD5) / Made available in DSpace on 2014-06-16T13:18:05Z (GMT). No. of bitstreams: 2 license_rdf: 23898 bytes, checksum: e363e809996cf46ada20da1accfcd9c7 (MD5) Dissertacao_AnaliseComputacionalCampos.pdf: 8199135 bytes, checksum: 4e41ee450e20c1b754db24b43b82d5fa (MD5) Previous issue date: 2008 / A simulação numérica do escoamento de ar em ambientes internos é na atualidade o método mais apropriado para análise de conforto térmico em ambientes internos. O escoamento de ar nesses ambientes configura-se como um escoamento complexo, pois, em regra geral, é uma combinação de escoamentos cisalhantes livres (jatos) e cisalhantes de parede, além disso, esses escoamentos são governados por forças de inércia e forças de empuxo, caracterizando-o como de convecção mista. A combinação desses mecanismos cria um escoamento com características complexas, como zonas de recirculação, vórtices, descolamento e recolamento de camada-limite dentre outras. Portanto, a precisão da solução estará diretamente ligada, principalmente, na habilidade do modelo de turbulência adotado de reproduzir as características turbulentas do escoamento de ar e da transferência térmica. O objetivo principal do presente trabalho foi a simulação computacional do ambiente térmico interno do galpão que abriga os geradores e motores Wärtzilä da Usina Termelétrica Santana no estado do Amapá. A formulação matemática baseada na solução das equações gerais de conservação inclui uma análise dos principais modelos de turbulência aplicados ao escoamento de ar em ambientes internos, assim como os processos de transferência de calor associados. Na modelagem numérica o método de volumes finitos é usado na discretização das equações de conservação, através do código comercial Fluent-Airpak, que foi usado nas simulações computacionais para a análise dos campos de velocidade e temperatura do ar. A utilização correta do programa computacional foi testada e validada para o problema através da simulação precisa de casos retirados da literatura. Os resultados numéricos foram comparados a dados obtidos de medições experimentais realizados no galpão e apresentou boa concordância, considerando a complexidade do problema simulado, o objetivo da simulação em face da diminuição da temperatura no interior do galpão e, também, em função das limitações encontradas quando da tomada das medições experimentais. Além disso, foram feitas simulações de estratégias de melhoria do ambiente térmico da Usina, baseadas na realidade levantada e nos resultados da simulação numérica. Finalmente, foram realizadas simulações do protótipo de solução proposto para a diminuição da temperatura interna do galpão o que possibilitará um aumento, na faixa de 20 a 30%, do tempo de permanência no interior do galpão. / The numerical simulation of the airflow in internal environments is in the present time the most appropriate method for analysis of thermal comfort indoors. The airflow in these environments is configured as a complex one, therefore, in general, it is a combination of free-shear flow (jet) and of wall-shear flow, moreover, these are governed by inertia and buoyancy forces, characterizing a situation of mixing convection. The combination of these mechanisms creates an airflow with complex characteristics, as recirculation zones, vortices, detachment and re-attachment of boundary layer amongst others. Therefore, the precision of the solution will be directly connected, mainly, with the ability of the adopted turbulence model to reproduce the turbulent characteristics of the airflow and thermal transfers. The main objective of the present work was the computational simulation of the internal thermal environment of the enclosure which shelters the generators and the Wärtzilä engines of the thermo-electric power plant of Santana in the state of Amapá (Brazil). The mathematical formulation based on the solution of the general equations of conservation includes an analysis of the principal models of turbulence applied to the airflow inside the enclosure, as well as the heat transfer processes associated. The finite-volume numerical method is used in the discretization of the conservation equations, through the Fluent-Airpak software, for the analysis of the distribution of air velocity and temperature fields. The correct use of the software was tested and validated by successfully simulating problems solved by other authors. The numerical results of the airflow in the enclosure were compared with the experimental data and presented a good agreement, by considering the complexity of the simulated problem and the limitations and difficulties found during measurements. Moreover, simulations are presented of strategies for improvement of the thermal environment, based on the actual reality and on the results of the numerical simulations. Finally, simulations of a prototype solution are presented with the reduction of the internal temperature in the enclosure. This solution allows an increase of the exposure time inside the enclosure, from 20 up to 30%, and improves the thermal comfort of the thermo-electric power plant.

Delayed auditory feedback (DAF) is known to produce speech disruptions in fluent speakers. The present study examined the relationship between individuals' susceptibility to DAF and their auditory processing skills. Forty participants (20 males and 20 females) read and produced monologue at no delay and 3 different delay levels of 100, 200, and 400 ms. Auditory processing skills were evaluated using dichotic digits test (DDT) and staggered spondaic word (SSW) test. Males produced significantly more Stuttering-Like Disfluencies (SLDs) under DAF than females. Significantly more SLDs were observed during conversation compared to reading. Overall, there was significant correlation between the frequency of SLDs and auditory performance on SSW test. Females scored significantly better on both SSW test and DDT compared to males. Scores on attention regulation questionnaire were not significantly different between genders. Fewer SLDs observed in females under DAF could be attributed to their superior control of auditory processing resources compared to males.

Ce travail a pour objectif de comprendre les mécanismes mis en jeu lors de l'application d'un gradient de champ magnétique sur le développement d'une flamme de diffusion laminaire décrochée. Les propriétés de ce type de flamme dépendent beaucoup des vitesses d'éjection, de la géométrie du brûleur et du nombre de Scmidt des carburants. Nous avons ici considéré une configuration d'une flamme laminaire de diffusion de méthane/air, issue d'un brûleur coaxial, débouchant dans de l'air ambiant. Le champ magnétique est généré par un aimant permanent. L'étude expérimentale montre que la hauteur de décrochage est très sensible au débit d'air mais peu au débit de méthane. L'application du champ magnétique permet de réduire la hauteur de décrochage et renforce la stabilité de la flamme. L'étude numérique a été conduite dans le cas sans et avec champ, à partir d'un code CFD dans lequel, deux modifications ont été apportées : ajout d'un modèle de rayonnement qui permet de prendre en compte les pertes radiatives des gaz chauds et prise en compte de l'influence du champ magnétique par l'ajout d'une force volumique dans l'équation de quantité de mouvement. Il a été montré que la hauteur de décrochage dépend fortement du débit d'air mais peu du débit de méthane. L'application du champ magnétique permet de réduire la vitesse de l'air et le gradient spatial de fraction massique de méthane, phénomènes importants dans la diminution de la hauteur de décrochage et dans l'augmentation de la vitesse de propagation de la flamme.

The heat transfer behavior of phase change material fluid under laminar flow conditions in circular tubes and internally longitudinal finned tubes are presented in this study. Two types of boundary conditions, including uniform axial heat flux with constant peripheral temperature and uniform axial and peripheral temperature, were considered in the case of circular tubes. An effective specific heat technique was used to model the phase change process assuming a hydrodynamically fully-developed flow at the entrance of the tube. Results were also obtained for the phase change process under hydro dynamically and thermally fully developed conditions. In case of a smooth circular tube with phase change material (PCM) fluid, results of Nusselt number were obtained by varying the bulk Stefan number. The Nusselt number results were found to be strongly dependent on the Stefan number. In the case of a finned tube two types of boundary conditions were studied. The first boundary condition had a uniform axial heat flux along the axis of the tube with a variable temperature on the peripheral surface of the tube. The second boundary condition had a constant temperature on the outer surface of the tube. The effective specific heat technique was again implemented to analyze the phase change process under both the boundary conditions. The Nusselt number was determined for a tube with two fins with different fin height ratios and fin thermal conductivity values. It was determined that the Nusselt number was strongly dependent on the Stefan number, fin thermal conductivity value, and height of the fins. It was also observed that for a constant heat axial flux boundary condition with peripherally varying temperature, the phase change slurry with the internally finned tube performed better than the one without fins. A similar trend was observed during the phase change process with internal fins under the constant wall temperature boundary condition.

In this thesis, a loosely coupled Fluid-Structure Interaction (FSI) analysis method is developed for the solution of steady state missile/rocket aeroelastic problems. FLUENT is used as the Computational Fluid Dynamics (CFD) tool to solve Euler equations whereas ANSYS is used as the Computational Structural Dynamics (CSD) tool to solve linear structural problem. The use of two different solvers requires exchanging data between fluid and structure domains at each iteration step. Kriging interpolation method is employed for the data transfer between non-coincident fluid and structure grids. For mesh deformation FLUENT&rsquo / s built-in spring based smoothing approach is utilized. The study is mainly divided into two parts. In the first part static aeroelastic analysis for AGARD 445.6 wing is conducted and the results are compared with the reference studies. Deformation and pressure coefficient results are compared with reference both of which are in good agreement. In the second part, to investigate possible effects of aeroelasticity on rocket and missile configurations, static aeroelastic analysis for a canard controlled generic slender missile which is similar to a conventional 2.75&rdquo / rocket geometry is conducted and results of the analysis for elastic missile are compared with the rigid case. It is seen that the lift force produced by canards and tails lessen due to deformations, stability characteristics of the missile decreases significantly and center of pressure location changes due to the deformations in the control surfaces.