<p> The pressure gradients for sphere trains in 1 in. and 2 in. pipes have been measured with water flowing past the stationary spheres at Reynolds numbers (based on pipe diameter) from to 4 - 105 , and sphere/pipe diameter ratios ranging from 0.486 - 0.84. Two dimensionless pressure ratios have been derived so that the experimental results obtained can be generalised to any pipe diameter with the above constraints on Reynolds number and diameter ratio. Drag coefficients have also been calculated from pressure drop measurements for the 0.84 diam. ratio spheres in· 1 in. pipe. These have been compared with McNoun's drag coefficient. </p> <p> The application of the results to predict pressure gradients for sphere trains in any pipe diameter has been illustrated. </p> / Thesis / Master of Engineering (MEngr)

Submitted by Marcele Costal de Castro (costalcastro@gmail.com) on 2017-10-04T17:13:38Z No. of bitstreams: 1 PAULO AUGUSTO BERQUÓ DE SAMPAIO D.pdf: 6576641 bytes, checksum: 71355f6eedcf668b2236d4c10f1a2551 (MD5) / Made available in DSpace on 2017-10-04T17:13:38Z (GMT). No. of bitstreams: 1 PAULO AUGUSTO BERQUÓ DE SAMPAIO D.pdf: 6576641 bytes, checksum: 71355f6eedcf668b2236d4c10f1a2551 (MD5) Previous issue date: 1991-09 / The basic difficulties associated with the numerical solution of the incompressible Navier-Stokes equations in primitive variables are identified and analysed. These difficulties, namely the lack of self-adjointness of the flow equations and the requirement of choosing compatible interpolations for velocity and pressure, are addressed with the development of consistent Petrov-Galerkin formulations. In particular, the solution of incompressible viscous flow problems using simple equal order interpolation for all variables becomes possible .

A comprehensive survey of available numerical methods and models was performed on the open source computational fluid dynamics solver OpenFOAM version 2.0 for incompressible turbulent bluff body flows. Numerical methods are illuminated using source code for side-by-side comparison. For validation, the accuracy of flow predictions over a sphere in the subcritical regime and delta wing with sharp leading edge is assessed. Solutions show mostly good agreement with experimental data and data obtained from commercial software. A demonstration of the numerical implementation of a dynamic hybrid RANS/LES framework is also presented, including results from test studies.

The utilization of steady state flow of air over tandem circular cylinders has several applications in engineering systems. Incompressible flow over circular cylinders in tandem at different spacing with and without plasma actuation on the leading cylinder will be investigated in this paper to understand the effects of plasma actuation on flow properties and wake region of the two cylinders in cross flow. The principal focus of the research is on the use of experimental and computational methods to study and provide valid results, the research will analyze the wake region, the effect of Reynolds number and the longitudinal spacing between cylinder on vortex shedding, aerodynamic parameters i.e. lift, drag, pressure differential, etc. The research will be conducted for steady flow at Reynold number, Re = U∞ L/v between 5000 and 8000 for air. The turbulence of the wake and dynamic instability of the experimental is characterized by the Strouhal number, St = fL/U∞ frequency of the vortex shedding in the wake which is directly proportional to the spacing, λ from center to center of cylinders between 3 to 5 inches. The dependencies on critical values of Re and St in symmetric flow over cylinders to show the instability of the flow regime in previous research. At Re = 5000 the vortex co-shedding on the second cylinder would occur at critical spacing, λccharacterized by the Re - St relationship at 3 ≤ λ ≤ 5 in the flow regime. The use of plasma actuation in fluid dynamics to control flow velocity by generating momentum to force atmospheric pressure and velocity in external flow with Single- Dielectric Barrier Discharge(SDBD) for both two and three-dimensional, 2D and 3D actuator (straight and segmented actuator). The SDBD actuators are mounted spanwise on the leading cylinder for both 2D and 3D to impact momentum, therefore, forcing the wake regime. Computational Analysis is utilized for result and data pre-processing. The steady three-dimensional flow of tandem cylinders can be studied through Large Eddy Simulation (LES) using a subgrid-scale model to compare numerical and experimental results for the same setup and physical conditions. Particle Image Velocimetry (PIV) is used to resolve time series images from flow visualization of the experiment, the images are processed to visualize velocity vectors of the flow regimes. The velocity profile of the flow can be averaged and plotted for all instantaneous time-series images processed in PIV by Dynamic Mode Decomposition (DMD) or Proper Orthogonal Decomposition (POD) to generate common eigenvalues and eigenvector of the large dimension PIV data which shows the average properties of the flow properties.

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Ce travail concerne l’écoulement incompressible et stationnaire autour d’un cylindre semi-infini en rotation, et ses propriétés de stabilité linéaire. L’effet de la courbure et de la rotation sur la stabilité de cet écoulement est étudié de manière systématique. Avant d’étudier la stabilité, nous calculons d’abord l’écoulement de base. A grand nombre de Reynolds, une couche limite se développe le long du cylindre, ce qui permet d’utiliser l’approximation de couche limite des équations de Navier–Stokes. Ces équations dépendent de deux paramètres de contrôle sans dimension, le nombre de Reynolds (Re) et le taux de rotation (S), et sont résolues numériquement pour obtenir les profils de vitesse et de pression pour une large gamme des paramètres de contrôle. Une couche limite initialement mince s’épaissit avec la distance axiale; ainsi, son épaisseur devient comparable et finalement plus importante que le rayon du cylindre. Au-delà d’un certain taux de rotation, les effets centrifuges conduisent `a un jet de paroi le long d’une portion du cylindre. L’extension axiale de ce jet augmente avec le taux de rotation. L’intensité du jet augmente aussi avec S. Des analyses asymptotiques de l’écoulement à grande distance axiale et à fort taux de rotation sont aussi présentées. L’analyse de stabilité linéaire du précédent écoulement est effectuée dans l’approximation locale. Après une décomposition en modes normaux, les équations des perturbations sont transformées en un problème de valeur propre `a fréquence complexe (ω). Ce problème dépend de cinq paramètres sans dimension: Re, S, la distance axiale normalisée (Z), le nombre d’onde axial (α) et le nombre d’onde azimutal (m). Les équations de stabilité sont résolues numériquement pour étudier les régions instables dans l’espace des paramètres. On observe que de faibles taux de rotation ont un effet important sur la stabilité de l’écoulement. Cette forte déstabilisation est associée à la présence d’un mode quasi-marginal pour le cylindre fixe et qui devient instable pour de petites valeurs de S. Ce phénomène est confirmé par une analyse en perturbation `a petit S. Sans rotation, l’écoulement est stable pour tout Re < 1060, et pour Z > 0.81. Mais, en présence d’une faible rotation, l’instabilité n’est plus limitée par une valeur minimale de Re ou un seuil en Z. Les courbes critiques dans le plan (Z, Re) sont calculées pour une large gamme de S et les conséquences pour la stabilité de l’écoulement discutées. Enfin, un développement asymptotique pour le nombre de Reynolds critique est obtenu, valable aux grandes valeurs de Z. / This work concerns the steady, incompressible flow around a semi-infinite, rotating cylinder and its linear-stability properties. The effect of cylinder curvature and rotation on the stability of this flow is investigated in a systematic manner. Prior to studying its stability, we first compute the basic flow. At large Reynolds numbers, a boundary layer develops along the cylinder. The governing equations are obtained using a boundary-layer approximation to the Navier–Stokes equations. These equations contain two non-dimensional control parameters: the Reynolds number (Re) and the rotation rate (S), and are numerically solved to obtain the velocity and pressure profiles for a wide range of control parameters. The initially thin boundary layer grows in thickness with axial distance, becoming comparable and eventually larger than the cylinder radius. Above a threshold rotation rate, a centrifugal effect leads to the presence of a wall jet for a certain range of streamwise distances. This range widens as the rotation rate increases. Furthermore, the wall jet strengthens as S increases. Asymptotic analyses of the flow at large streamwise distances and at large rotation rates are presented. A linear stability analysis of the above flow is carried out using a local-flow approximation. Upon normal-mode decomposition, the perturbation equations are transformed to an eigenvalue problem in complex frequency (ω). The problem depends on five non-dimensional parameters: Re, S, scaled streamwise direction (Z), streamwise wavenumber (α) and azimuthal wavenumber m. The stability equations are numerically solved to investigate the unstable regions in parameter space. It is found that small amounts of rotation have strong effects on flow stability. Strong destabilization by small rotation is associated with the presence of a nearly neutral mode of the non-rotating cylinder, which becomes unstable at small S. This is further quantified using smallS perturbation theory. In the absence of rotation, the flow is stable for all Re below 1060, and for Z above 0.81. However, in the presence of small rotation, the instability becomes unconstrained by a minimum Re or a threshold in Z. The critical curves in the (Z, Re) plane are computed for a wide range of S and the consequences for stability of the flow described. Finally, a large-Z asymptotic expansion of the critical Reynolds number is obtained.

Problemas de otimização se fazem cada vez mais presentes nos mais diversos ramos da Engenharia. Encontrar configurações ótimas para um determinado problema significa, por exemplo, melhorar desempenho, reduzir custos entre outros ganhos. Existem hoje diversas maneiras de atacar um problema de otimização, cada qual com suas particularidades, vantagens e desvantagens. Dentre os métodos de otimização que utilizam gradientes de sensibilidade, o cálculo numérico dos mesmos consiste em uma importante etapa do projeto que, dependendo do problema, pode acarretar em custos computacionais muito elevados inviabilizando a abordagem escolhida. Este trabalho visa desenvolver e apresentar uma nova metodologia para o cálculo desses gradientes de sensibilidade, com base no Método Adjunto. O Método Adjunto é um método amplamente estudado e com diversas aplicações principalmente em Engenharia Aeronáutica. Nesse trabalho, todo o conhecimento prévio é utilizado para a derivação do método para aplicá-lo a escoamentos viscosos e incompressíveis. É desenvolvido também o cálculo do gradiente de sensibilidade com respeito a parâmetros geométricos e não geométricos. Para validar a metodologia proposta são feitas simulações numéricas das equações governantes do escoamento e adjuntas utilizando dois códigos computacionais distintos, SEMTEX e FreeFem++, o primeiro baseado no Método dos Elementos Espectrais e o segundo no Método dos Elementos Finitos, mostrando assim a independência do Método Adjunto na sua formulação contínua em relação a métodos computacionais. Para a validação são cujos gradientes possam ser calculados de outras formas permitindo comparações para calibrar e aperfeiçoar o cálculo do gradiente de sensibilidade. / Optimization problems are widely present in differents fields of Engineering. Finding optimal configurations in a problem means, for example, improving performance, reducing costs, among other achievements. There are several wellknown ways to tackle an optimization problem, each one has its own advantages and disadvantages. Considering the gradient-based optimization methods, the step of their numerical calculation is extremely important, as it may result in huge computational costs, thus making the chosen method impracticable. This work aims to develop and present a new methodology to compute these sensitivity gradients based on the Adjoint Method. The Adjoint Method is a widely studied method with several applications chiefly in A eronautical Engineering. In the present work, all the previous knowledge will be used to derive the equations of the method in order to apply them to viscous incompressible flows. The calculation of the sensitivity gradient, with respect to both geometric and non-geometric paramatersm will be developed as well. To validate the proposed methodology, numerical simulations of the governing and adjoint equations are carried out, using two computational codes called SEMTEX and FreeFem++, the former is based on the Spectral Element Method and the later, on the Finite Element Method, thus showing that the Adjoint Method, in its continuous formulation, is independent of the particular numerical method that is used. In order to validate the algorithm, simple problems are chosen, for which the gradients can be computed by other methods. This choice admits comparison between numerical values of gradients in order to calibrate and improve the methodology proposed.

In the subject of Computational Fluid Dynamics (CFD), there seems to be small number of important progress in the pressure-based methods for several decades. Recent studies on the implicit coupled algorithms for pressure-based methods have brought a new insight. This method seems to provide a huge reduction in the solution times over segregated methods. Fully implicit coupled algorithm for pressure-based methods is very new subject with only few papers in literature. One of the most important work in this area is referenced as [1] in this thesis. Another source of information about the method comes from a commercially available code FLUENT which includes the algorithm as an option for pressure-based solver. However the algorithm in FLUENT does not seem to be a fully implicit with a little information in its manual. In this thesis, a fully implicit coupled pressure-based solver is developed mainly based on the available literature. The developed code is succesfully tested against some test cases.

We consider the application of high-order spectral/hp finite element technology to the numerical solution of boundary-value problems arising in the fields of fluid and solid mechanics. For many problems in these areas, high-order finite element procedures offer many theoretical and practical computational advantages over the low-order finite element technologies that have come to dominate much of the academic research and commercial software of the last several decades. Most notably, we may avoid various forms of locking which, without suitable stabilization, often plague low-order least-squares finite element models of incompressible viscous fluids as well as weak-form Galerkin finite element models of elastic and inelastic structures. The research documented in this dissertation includes applications of spectral/hp finite element technology to an analysis of the roles played by the linearization and minimization operators in least-squares finite element models of nonlinear boundary value problems, a novel least-squares finite element model of the incompressible Navier-Stokes equations with improved local mass conservation, weak-form Galerkin finite element models of viscoelastic beams and a high-order seven parameter continuum shell element for the numerical simulation of the fully geometrically nonlinear mechanical response of isotropic, laminated composite and functionally graded elastic shell structures. In addition, we also present a simple and efficient sparse global finite element coefficient matrix assembly operator that may be readily parallelized for use on shared memory systems. We demonstrate, through the numerical simulation of carefully chosen benchmark problems, that the finite element formulations proposed in this study are efficient, reliable and insensitive to all forms of numerical locking and element geometric distortions.

Made available in DSpace on 2014-10-09T12:50:37Z (GMT). No. of bitstreams: 0 / Made available in DSpace on 2014-10-09T13:58:52Z (GMT). No. of bitstreams: 1 00621.pdf: 16649575 bytes, checksum: 34a61ca5ff67945244a79765b98ddb45 (MD5) / Tese (Doutoramento) / IEA/T / University of London