This work is focused on computer simulations of fractal capacitors. The geometry of capacitors and its influence is investigated. Simulations are realized in programs Matlab, SolidWorks and Comsol Multiphysics. There are also several specific examples of different geometrics of capacitors their comparisons and assessment.

La méso-combustion est le régime de combustion où la taille caractéristique du domaine est juste supérieure à la distance de coincement de la flamme , typiquement de l'ordre du centimètre. La difficile réalisation de systèmes de combustion fonctionnant en ce régime de flamme particulier suscite l'intérêt : il devient alors possible de tirer parti de la haute densité énergétique des hydrocarbures pour concevoir des systèmes de production d'énergie plus compacts. Nous nous intéressons à la réalisation de calculs DNS compressibles d'une chambre de combustion cubique de 8 x 10 x 8 mm3. Ce travail présente autant la mise en œuvre des calcules, en particulier la problématique de la condition frontière mur, que les résultats obtenus. Ces derniers nous permettent d'analyser la phénoménologie complexe de cet écoulement réactif confiné et serviront de base à des modélisations futures. / Meso-combustion can be defined as the combustion regime where the involved lenghts scales are close but slightly larger than the quenching distance of the flame, tipically smaller than a cm. By taking advantage of the high energetic density of liquid hydrocarbons, it would become possible to build small-sized combustion-based long-lived lighter electrical power systems. However combsution phenomena at these meso-scales have their own shortcomings. Indeed, by decreasing the system size, the usual phenomenological balance betwenne chemical reactions, mixing, turbulence and heat transfer is changed. In the present work, we focus on the DNS calculation of a cubic meso-combsution chamber of 8 x 10 x 8 mm3. This works presents the implementation of the numerical strategy used, with a specific attention to the no-slip wall compressible boundary condition. We then present an analysis of this particular reactive flow. The results are useful for future modeling of such a combustor.

Orientador: José Manoel Balthazar / Resumo: A microscopia da força atômica (AFM) com medidas em nanoescala, vêm da nanotecnologia e constitui atualmente um campo de pesquisa multidisciplinar. A proposta de pesquisa apresentada tem como objetivo contribuir a pesquisa cientifica sobre AFM considerando que sistema está operando no modo intermitente e em meio líquido, e que a dinâmica do amortecimento do meio líquido é determinado por derivadas de ordem fracionária. Através de ferramentas de simulação numérica serão realizadas a análise dinâmica do sistema para os casos em que o sistema tenha comportamento caótico. Para supressão deste comportamento caótico serão utilizadas e analisadas duas estratégias de controle, o controle SDRE (Estados Dependentes da Equação de Riccati) e o controle OLFC (Controle Linear por Realimentação Ótimo). / Abstract: The atomic force microscope (AFM) with nanoscale measurements comes from nanotechnology and is currently a multidisciplinary field of research. The present research proposal aims to contribute to scientific research on AFM considering that the system is operating in the intermittent mode and in liquid medium, and that the damping dynamics of the liquid medium is represented by fractional order derivatives. Through numerical simulation tools, the dynamic analysis of the system will be performed in cases where the system has chaotic behavior. To suppress this chaotic behavior we will use and analyze two control strategies, the SDRE (Riccati Equation Dependent States) and OLFC (Linear Control for Optimum Feedback). / Doutor

In this thesis, we present results of a numerical modelling study focused on the thermal evolution of the Earth and terrestrial planets. We focus particularly on two problems: I) constraining the internal structure of Venus and Mercury using their geoid and surface topography data and II) evaluating the effects of a rhe- ologically distinct post-perovskite on the secular cooling of the Earth. In part I, we performed simulations in a broad group of models of the Venusian man- tle, characterised by different rheological descriptions, and we compared spectra of their geoid and their surface topography with the observed quantities. Our analysis suggested that the geoid and the surface topography of Venus are con- sistent with a radially symmetric viscosity model with a strong 200 km thick lithosphere, without an asthenosphere and with a gradual viscosity increase in the underlying mantle. In the case of Mercury, none of our models was able to predict observed data, thus suggesting other than a dynamic origin of observed geoid and topography. In part II, we investigated style of Earth's mantle con- vection and its long-term evolution in the models that take into account a weak post-perovskite. We conclude that the presence of the weak post-perovskite en- hances the core cooling. This effect is comparable in...

The development in structural design and construction of high-speed craft has been extensive during the last decades. Environmental and economical issues have increased the need to develop more optimized structures, using new material concepts, to reduce weight and increase performance efficiency. However, both lack of, and limitations in design methodology, makes this a difficult task. In this thesis a methodological framework which enables detailed studies of the slamming loads and associated responses for high-speed planing craft in irregular waves is established. The slamming loads can either be formulated based on numerical simulations, or on experimental measurements and pressure distribution reconstruction. Structure responses are derived in the time-domain using finite element analysis. Statistical methods are used to determine design loads and lifetime extreme responses. The framework is applied to perform phenomenological studies of the slamming loading conditions for high-speed craft, and used to highlight and quantify the limitations in the prevailing semi-empirical method for design load determination with respect to slamming. A number of clarifications regarding the original derivation and the applicability of the prevailing semi-empirical method are presented. Finally, several potential improvements to the method are presented and the associated implications discussed. The long-term goal of the research project is to establish a method for direct calculation of loads and response for high-speed planing craft, which can enable design of truly efficient craft structures. The methodology and the results presented in this thesis are concluded to be important stepping-stones towards this goal. / <p>In page VII, Paper B is wrong title. The correct title is "Experiental Evaluation of Slamming Pressure Models Used in Structural Design of High-Speed Craft". QC 20130228</p>

Automotive parts may be the cause of very annoying friction-induced noise and the source of many customer complaints. Indeed, when a wiper operates on a windshield, vibratory phenomena may appear due to flutter instabilities and may generate squeal noise. As squeal noise generated by wiper system is a random and complex phenomenon, there are only few studies dealing with the wiper noise. The complexity of this phenomenon is due to the cinematic of the movement and to the various environmental parameters which have an influence on the appearance of the noise. This master thesis is a research and development project and presents a numerical simulation methodology used in the aim to reduce and eradicate squeal noise of wiper systems.  In the first part, the finite element model representing a wiper system and the numerical simulation methodology will be presented in detail. In the second part, stability analysis will be carried out in nominal studies and in designs of experiments. Parametric studies will also be achieved to understand the behavior and the influence of each considered input parameters. Two wiper blades, with the same geometry but with different material, will be considered for the different studies. These two wiper blades will be examined to figure out when squeal noises appear.

<p>U tezi je predstavljena implementacija metode teorija funkcionala gustine (DFT) bazirana na metodi za sklapanje naelektrisanja (CPM) koja koristi bazise gausijanskih funkcija. Metod je baziran na pretpostavci da se elektronska gustina naelektrisanja velikih sistema, može predstaviti kao suma doprinosa pojedinačnih atoma, takozvanih motiva gustine naelektrisanja, koji se dobijaju računanjem malog prototip sistema. Talasna funkcija,<br />kao i gustina naelektrisanja, se u na&scaron;oj implementaciji reprezentuju uz pomoć bazise gausijanskih funkcija, dok se motivi opisuju kori&scaron;ćenjem prostornih koordinata. Uz pomoć procedure za minimizaciju se iz motiva opisanih koordinatama, dobija gustina naelektrisanja predstavljena u bazisu Gausijana. Implementacija serijskog programa pokazuje značajno pobolj&scaron;anje u performansama u odnosu na prethodne implementacije bazirane na ravnim talasima. Ova implementacija re&scaron;ava sistem od približno 1000 atoma na jednom procesorskom jezgru za svega nekoliko sati. Paralelna implementacija uz pomoć naprednih metoda paralelizacije i distribucije podataka omogućava re&scaron;avanje sistema od vi&scaron;e desetina hiljada atoma. Najveći testirani sistem ima približno<br />20000 atoma i testiran je na 256 paralelnih procesa.</p> / <p>We present the implementation of the density functional theory (DFT) based charge patching method (CPM) using the basis of Gaussian functions. The method is based on the assumption that the electronic charge density of a large system is the sum of contributions of individual atoms, so called charge density motifs, that are obtained from calculations of small prototype systems.In our implementation wave functions and electronic charge density are represented using the basis of Gaussian functions, while charge density motifs are represented using a real space grid. A constrained minimization procedure is used to obtain Gaussian basis representation of charge density from real space representation of motifs. The code based on this&nbsp; implementation exhibits superior performance in comparison to previous implementation of the charge patching method using the basis of plane waves. It enables calculations of electronic structure of systems with around 1000 atoms on a single CPU core with computational time of just several hours. The parallel implementation enables calculations for the system with more than ten thousand atoms. The largest system tested has around 20000 atoms and was computed on 256 parallel processes.</p>

Many systems designed by electrical & computer engineers rely on electromagnetic (EM) signals to transmit, receive, and extract either information or energy. In many cases, these systems are large and complex. Their accurate, cost-effective design requires high-fidelity computer modeling of the underlying EM field/material interaction problem in order to find a design with acceptable system performance. This modeling is accomplished by projecting the governing Maxwell equations onto finite dimensional subspaces, which results in a large matrix equation representation (Zx = b) of the EM problem. In the case of integral equation-based formulations of EM problems, the M-by-N system matrix, Z, is generally dense. For this reason, when treating large problems, it is necessary to use compression methods to store and manipulate Z. One such sparse representation is provided by so-called H^2 matrices. At low-to-moderate frequencies, H^2 matrices provide a controllably accurate data-sparse representation of Z. The scale at which problems in EM are considered ``large'' is continuously being redefined to be larger. This growth of problem scale is not only happening in EM, but respectively across all other sub-fields of computational science as well. The pursuit of increasingly large problems is unwavering in all these sub-fields, and this drive has long outpaced the rate of advancements in processing and storage capabilities in computing. This has caused computational science communities to now face the computational limitations of standard linear algebraic methods that have been relied upon for decades to run quickly and efficiently on modern computing hardware. This common set of algorithms can only produce reliable results quickly and efficiently for small to mid-sized matrices that fit into the memory of the host computer. Therefore, the drive to pursue larger problems has even began to outpace the reasonable capabilities of these common numerical algorithms; the deterministic numerical linear algebra algorithms that have gotten matrix computation this far have proven to be inadequate for many problems of current interest. This has computational science communities focusing on improvements in their mathematical and software approaches in order to push further advancement. Randomized numerical linear algebra (RandNLA) is an emerging area that both academia and industry believe to be strong candidates to assist in overcoming the limitations faced when solving massive and computationally expensive problems. This thesis presents results of recent work that uses a random sampling method (RSM) to implement algebraic operations involving multiple H^2 matrices. Significantly, this work is done in a manner that is non-invasive to an existing H^2 code base for filling and factoring H^2 matrices. The work presented thus expands the existing code's capabilities with minimal impact on existing (and well-tested) applications. In addition to this work with randomized H^2 algebra, improvements in sparse factorization methods for the compressed H^2 data structure will also be presented. The reported developments in filling and factoring H^2 data structures assist in, and allow for, the further pursuit of large and complex problems in computational EM (CEM) within simulation code bases that utilize the H^2 data structure.

Les situations dans lesquelles une onde de choc interagit avec une couche limite sont nombreuses dans les industries aéronautiques et spatiales. Sous certaines conditions (nombre de Mach élevé, grand angle de choc…), ces interactions entrainent un décollement de la couche limite. Des études antérieures ont montré que la zone de recirculation et le choc réfléchi sont tous deux soumis à un mouvement d'oscillation longitudinale à basse fréquence connu sous le nom d’instabilité de l’interaction onde de choc / couche limite (IOCCL). Ce phénomène appelé soumet les structures à des chargement oscillants à basse fréquence qui peuvent endommager les structures.L’objectif du travail de thèse est de réaliser des simulations instationnaires de l’IOCCL afin de contribuer à une meilleure compréhension de l’instabilité de l’IOCCL et des mécanismes physiques sous-jacents.Pour effectuer cette étude, une approche numérique originale est utilisée. Un schéma « One step » volume fini qui couple l’espace et le temps, repose sur une discrétisation des flux convectifs par le schéma OSMP développé jusqu’à l’ordre 7 en temps et en espace. Les flux visqueux sont discrétisés en utilisant un schéma aux différences finies centré standard. Une contrainte de préservation de la monotonie (MP) est utilisée pour la capture de choc. La validation de cette approche démontre sa capacité à calculer les écoulements turbulents et la grande efficacité de la procédure MP pour capturer les ondes de choc sans dégrader la solution pour un surcoût négligeable. Il est également montré que l’ordre le plus élevé du schéma OSMP testé représente le meilleur compromis précision / temps de calcul. De plus un ordre de discrétisation des flux visqueux supérieur à 2 semble avoir une influence négligeable sur la solution pour les nombres de Reynolds relativement élevés considérés.En simulant un cas d’IOCCL 3D avec une couche limite incidente laminaire, l’influence des structures turbulentes de la couche limite sur l’instabilité de l’IOCCL est supprimée. Dans ce cas, l’unique cause d’IOCCL suspectée est liée à la dynamique de la zone de recirculation. Les résultats montrent que seul le choc de rattachement oscille aux fréquences caractéristiques de la respiration basse fréquence du bulbe de recirculation. Le point de séparation ainsi que le choc réfléchi ont une position fixe. Cela montre que dans cette configuration, l’instabilité de l’IOCCL n’a pas été reproduite.Afin de reproduire l’instabilité de l’IOCCL, la simulation de l’interaction entre une onde de choc et une couche limite turbulente est réalisée. Une méthode de turbulence synthétique (Synthetic Eddy Method - SEM) est développée et utilisée à l’entrée du domaine de calcul pour initier une couche limite turbulente à moindre coût. L’analyse des résultats est effectuée en utilisant notamment la méthode snapshot-POD (Proper Orthogonal Decomposition). Pour cette simulation, l’instabilité de l’IOCCL a été reproduite. Les résultats suggèrent que la dynamique du bulbe de recirculation est dominée par une respiration à moyenne fréquence. Ces cycles successifs de remplissage / vidange de la zone séparée sont irréguliers dans le temps avec une taille maximale du bulbe de recirculation variant d’un cycle à l’autre. Ce comportement du bulbe de recirculation traduit une modulation basse fréquence des amplitudes des oscillations des points de séparation et de recollement et donc une respiration basse fréquence de la zone séparée. Ces résultats suggèrent que l’instabilité de l’IOCCL est liée à cette dynamique basse fréquence du bulbe de recirculation, les oscillations du pied du choc réfléchi étant en phase avec le point de séparation. / Situations where an incident shock wave impinges upon a boundary layer are common in the aeronautical and spatial industries. Under certain circumstances (High Mach number, large shock angle...), the interaction between an incident shock wave and a boundary layer may create an unsteady separation bubble. This bubble, as well as the subsequent reflected shock wave, are known to oscillate in a low-frequency streamwise motion. This phenomenon, called the unsteadiness of the shock wave boundary layer interaction (SWBLI), subjects structures to oscillating loads that can lead to damages for the solid structure integrity.The aim of the present work is the unsteady numerical simulation of (SWBLI) in order to contribute to a better understanding of the SWBLI unsteadiness and the physical mechanism causing these low frequency oscillations of the interaction zone.To perform this study, an original numerical approach is used. The one step Finite Volume approach relies on the discretization of the convective fluxes of the Navier Stokes equations using the OSMP scheme developed up to the 7-th order both in space and time, the viscous fluxes being discretized using a standard centered Finite-Difference scheme. A Monotonicity-Preserving (MP) constraint is employed as a shock capturing procedure. The validation of this approach demonstrates the correct accuracy of the OSMP scheme to predict turbulent features and the great efficiency of the MP procedure to capture discontinuities without spoiling the solution and with an almost negligible additional cost. It is also shown that the use of the highest order tested of the OSMP scheme is relevant in term of simulation time and accuracy compromise. Moreover, an order of accuracy higher than 2-nd order for approximating the diffusive fluxes seems to have a negligible influence on the solution for such relatively high Reynolds numbers.By simulating the 3D unsteady interaction between a laminar boundary layer and an incident shock wave, we suppress the suspected influence of the large turbulent structures of the boundary layer on the SWBLI unsteadiness, the only remaining suspected cause of unsteadiness being the dynamics of the separation bubble. Results show that only the reattachment point oscillates at low frequencies characteristic of the breathing of the separation bubble. The separation point of the recirculation bubble and the foot of the reflected shock wave have a fixed location along the flat plate with respect to time. It shows that, in this configuration, the SWBLI unsteadiness is not observed.In order to reproduce and analyse the SWBLI unsteadiness, the simulation of a shock wave turbulent boundary layer interaction (SWTBLI) is performed. A Synthetic Eddy Method (SEM), adapted to compressible flows, has been developed and used at the inlet of the simulation domain for initiating the turbulent boundary layer without prohibitive additional computational costs. Analyses of the results are performed using, among others, the snapshot Proper Orthogonal Decomposition (POD) technique. For this simulation, the SWBLI unsteadiness has been observed. Results suggest that the dominant flapping mode of the recirculation bubble occurs at medium frequency. These cycles of successive enlargement and shrinkage of the separated zone are shown to be irregular in time, the maximum size of the recirculation bubble being submitted to discrepancies between successive cycles. This behaviour of the separation bubble is responsible for a low frequency temporal modulation of the amplitude of the separation and reattachment point motions and thus for the low frequency breathing of the separation bubble. These results tend to suggest that the SWBLI unsteadiness is related to this low frequency dynamics of the recirculation bubble; the oscillations of the reflected shocks foot being in phase with the motion of the separation point.

The lattice Boltzmann method (LBM) is widely studied andused in the last years to replace the conventional numerical solvers forthe Navier-Stokes equations. In this work, a general introduction tofluid dynamics equations and the changes when the flow is a reactivemulti-species one will be given first. The lattice Boltzmann method andalgorithm will then be explained in details with the kinetic theorybehind, tested and validated for canonical test cases of doubly shearlayer flow in reactive and non-reactive flows. Finally the method willbe applied to simulate a non-reacting propane jet and the results willbe validated using experimental data. The objectives of this thesis are mainly: first a better understandingof the LBM, the combustion reactions, the jets and how they work, secondthe use of this method to produce a simple code that works for a basictest case, third validate this code with more developed methods, andfinally apply this method to simulate a more complex configuration whichis the non-reacting propane jet flame into co-flowing air / Gitter Boltzmann-metoden LBM studeras och används i stor utsträckning under de senaste åren för att ersätta de konventionella numeriska lösare för Navier-Stokes ekvationer.I detta arbete kommer en allmän introduktion till vätskedynamikekvationer och förändringarna när flödet är en reaktiv multiart att ges först.Gitter Boltzmann metod och algoritm kommer sedan att förklaras i detaljer med kinetisk teori bakom, testas och valideras för kanoniska testfall av dubbelt savskikt flöde i reaktiva och icke-reaktiva flöden.Slutligen kommer metoden att tillämpas för att simulera en icke-reagerande propanstråle och resultaten kommer att valideras med hjälp av experimentella data.\\ \\ Målen för denna avhandling är främst: först en bättre förståelse av LBM, förbränningsreaktionerna, jetstrålarna och hur de fungerar, för det andra användningen av denna metod för att producera en enkel kod som fungerar för ett grundläggande testfall, tredje validera denna kod med mer utvecklade metoder och slutligen tillämpa denna metod för att simulera en mer komplex konfiguration som är den icke-reagerande propanstrålelågan i co-flowing luft.