L'objectif de ce travail de thèse est le développement d'une approximation polynomiale axiale dans un solveur basé sur la Méthode des Caractéristiques. Le contexte, est celui de la solution stationnaire de l'équation de transport des neutrons pour des systèmes critiques, et l'implémentation pratique a été réalisée dans le solveur "Two/three Dimensional Transport" (TDT), faisant partie du projet APOLLO3®. Un solveur MOC pour des géométries en trois dimensions a été implémenté dans ce code pendant un projet de thèse antécédent, se basant sur une approximation constante par morceaux du flux et des sources des neutrons. Les développements présentés dans la suite représentent la continuation naturelle de ce travail. Les solveurs MOC en trois dimensions sont capables de produire des résultats précis pour des géométries complexes. Bien que précis, le coût computationnel associé à ce type de solveur est très important. Une représentation polynomiale en direction axiale du flux angulaire des neutrons a été utilisée pour réduire ce coût computationnel.Le travail réalisé pendant cette thèse peut être considéré comme divisé en trois parties: transport, accélération et autres. La première partie est constituée par l'implémentation de l'approximation polynomiale choisie dans les équations de transmission et de bilan typiques de la Méthode des Caractéristiques. Cette partie a aussi été caractérisée par le calcul d'une série de coefficients numériques qui se sont révélés nécessaires afin d'obtenir un algorithme stable. Pendant la deuxième partie, on a modifié et implémenté la solution des équations de la méthode d'accélération DPN. Cette méthode était déjà utilisée pour l'accélération et des itérations internes et externes dans TDT pour les solveurs deux et trois dimensionnels avec l'approximation des flux plat, quand ce travail a commencé. L'introduction d'une approximation polynomiale a demandé plusieurs développements numériques regardant la méthode d'accélération. Dans la dernière partie de ce travail on a recherché des solutions pour un mélange de différents problèmes liés aux premières deux parties. En premier lieux, on a eu à faire avec des instabilités numériques associées à une discrétisation spatiale ou angulaire pas suffisamment précise, soit pour la partie transport que pour la partie d'accélération. Ensuite, on a essayé d'utiliser différentes méthodes pour réduire l'empreinte mémoire des coefficients d'accélération. L'approche qu'on a finalement choisie se base sur une régression non-linéaire au sens des moindres carrés de la dépendance en fonction des sections efficaces typique de ces coefficients. L'approche standard consiste dans le stockage d'une série de coefficients pour chaque groupe d'énergie. La méthode de régression permet de remplacer cette information avec une série de coefficients calculés pendant la régression qui sont utilisés pour reconstruire les matrices d'accélération au cours des itérations. Cette procédure ajoute un certain coût computationnel à la méthode, mais nous pensons que la réduction de la mémoire rende ce surcoût acceptable.En conclusion, le travail réalisé a été concentré sur l'application d'une simple approximation polynomiale avec l'objectif de réduire le coût computationnel et l'empreinte mémoire associées à un solveur basée sur la Méthodes des Caractéristiques qui est utilisé pour calculer le flux neutroniques pour des géométries à trois dimensions extrudées. Même si cela ne constitue pas une amélioration radicale des performances, l'approximation d'ordre supérieur qu'on a introduit permet une réduction en termes de mémoire et de temps de calcul d'un facteur compris entre 2 et 5, selon le cas. Nous pensons que ces résultats constitueront une base fertile pour des futures améliorations. / The purpose of this PhD is the implementation of an axial polynomial approximation in a three-dimensional Method Of Characteristics (MOC) based solver. The context of the work is the solution of the steady state Neutron Transport Equation for critical systems, and the practical implementation has been realized in the Two/three Dimensional Transport (TDT) solver, as a part of the APOLLO3® project. A three-dimensional MOC solver for 3D extruded geometries has been implemented in this code during a previous PhD project, relying on a piecewise constant approximation for the neutrons fluxes and sources. The developments presented in the following represent the natural continuation of this work. Three-dimensional neutron transport MOC solvers are able to produce accurate results for complex geometries. However accurate, the computational cost associated to this kind of solvers is very important. An axial polynomial representation of the neutron angular fluxes has been used to lighten this computational burden.The work realized during this PhD can be considered divided in three major parts: transport, acceleration and others. The first part is constituted by the implementation of the chosen polynomial approximation in the transmission and balance equations typical of the Method Of Characteristics. This part was also characterized by the computation of a set of numerical coefficients which revealed to be necessary in order to obtain a stable algorithm. During the second part, we modified and implemented the solution of the equations of the DPN synthetic acceleration. This method was already used for the acceleration of both inners and outers iteration in TDT for the two and three dimensional solvers at the beginning of this work. The introduction of a polynomial approximation required several equations manipulations and associated numerical developments. In the last part of this work we have looked for the solutions of a mixture of different issues associated to the first two parts. Firstly, we had to deal with some numerical instabilities associated to a poor numerical spatial or angular discretization, both for the transport and for the acceleration methods. Secondly, we tried different methods to reduce the memory footprint of the acceleration coefficients. The approach that we have eventually chosen relies on a non-linear least square fitting of the cross sections dependence of such coefficients. The default approach consists in storing one set of coefficients per each energy group. The fit method allows replacing this information with a set of coefficients computed during the regression procedure that are used to re-construct the acceleration matrices on-the-fly. This procedure of course adds some computational cost to the method, but we believe that the reduction in terms of memory makes it worth it.In conclusion, the work realized has focused on applying a simple polynomial approximation in order to reduce the computational cost and memory footprint associated to a Method Of Characteristics solver used to compute the neutron fluxes in three dimensional extruded geometries. Even if this does not a constitute a radical improvement, the high order approximation that we have introduced allows a reduction in terms of memory and computational times of a factor between 2 and 5, depending on the case. We think that these results will constitute a fertile base for further improvements.

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With the continuous growth of the space industry and the introduction of reusable rockets, the number of rocket launches is expected to increase significantly in the following years. During rocket launching, the engine exhaust impinges on the launch structure producing a complex flow field. The rocket jet induces large thermoaerodynamic and acoustic loads on the launch structures and the rocket. This thesis aims to study the physics and numerical considerations behind supersonic flows exhausted from rocket engines. First, the treatment of turbulent compressible flows through the Favre-averaged equations and the SST k-ω model are studied. Next, the numerical modeling of the problem, including solver and meshing theory is presented. Then, a model of a nozzle is explained along with how the performance is assessed to finally design a M=3 two-dimensional nozzle using the method of characteristics (MOC). The two-dimensional results are validated using Ansys Fluent, and the same geometry is used for the following axisymmetrical problems, which include the study of a free and impinging jet. The free jet problem serves to study how the nozzle behaves in a two-dimensional axisymmetric problem and to validate the impinging jet results. To obtain the results, RANS-based simulations of a cold, over-expanded jet with adiabatic walls are performed. Empirical formulas were used to verify the results. Lastly, the impinging jet problem is simulated using the same inlet boundary conditions as for the free jet. The impact that the plate distance to the exit of the nozzle has on the position of the shock waves when the jet impinges on the flat surface is assessed. Finally, an optimization of the shape of a wedge to minimize the maximum turbulence kinetic energy produced during steady-state simulation is carried out. As an appendix to the work, an aeroacoustic study of the impinging jet at 4De distance is presented. The results show the direction of propagation of the acoustic waves but due to the lack of acoustic quality of the mesh, the predicted sound pressure levels do not match the expected behavior.

Yes / A dam break wave caused by the discontinuity in depth and velocity of a flow is resulted from instantaneous release a body of water from a channel and classified naturally as a rapidly varied unsteady flow. Due to its nature, it is hard to be accurately represented by analytical models. The aim of this study is to establish the modelling differences and complexity echelons between analytically simulated explicit laminar and turbulent dry bed dam break wave free surface profiles. An in-depth solution to the free surface profile has been provided and evaluated by representing the reported dam break flow measurements at various locations. The methodology adopted utilizes the free surface profile formulations presented by Chanson 1,2, which are developed using the method of characteristics. In order to validate the results of the presented analytical models in illustrating the dam break wave under dry bed conditions, published experimental data provided by Schoklitsch 3, Debiane 4 and Dressler 5 are used to compare and analyze the performance of the dam break waves under laminar and turbulent flow conditions.

A dual-axis fluidic thrust vectoring (FTV) system is proposed where the supersonic propulsive jet of an aircraft is exhausted over a scarfed (swept), curved surface to produce flight control moments in both the pitch and yaw axes. This work contributes towards practical dual-axis FTV through expansion of fundamental curved-wall jet (CWJ) understanding, development of the novel Superimposed Characteristics technique for supersonic nozzle design, and performance evaluation of an experimental scarfed curved wall FTV configuration. Previous work has suggested that the use of a sheared exhaust velocity profile improves the attachment of supersonic jets to curved surfaces; however, evidence to support this is limited. To address this, an inviscid numerical CWJ model was developed using the two-dimensional method of characteristics. A major outcome is improved understanding of the effect of exhaust velocity profile on CWJ wave structure and subsequent jet attachment. A sheared velocity exhaust is shown to generate a wave structure that diminishes adverse streamwise pressure gradients within a supersonic curved-wall jet. This reduces the likelihood of boundary layer separation and as a result, a sheared exhaust velocity CWJ is expected to be less readily separated compared to other exhaust velocity profiles. A novel method termed Superimposed Characteristics was developed for the low-order design of supersonic nozzles with rectangular exits. The technique is capable of generating 3D nozzle geometries based on independent exit plane orientation and exhaust velocity distribution requirements. The Superimposed Characteristics method was used to design scarfed rectangular exit nozzles with sheared velocity exhaust profiles. These nozzles were then evaluated using finite volume computational methods and experimental methods. From the analysis, the Superimposed Characteristics method is shown to be valid for preliminary nozzle design. Experimental methods were used to study the on- and off-design attachment qualities of uniform and sheared velocity exhaust jets for a FTV configuration with an external curved wall termination angle of 90 degrees and scarf angle of 30 degrees. Experiments at the on-design nozzle pressure ratio (NPR) of 3.3 demonstrated pitch and yaw jet deflection angles of 78 degrees and 23 degrees respectively for the uniform exhaust velocity CWJ. The sheared exhaust velocity CWJ achieved lower pitch and yaw deflection angles of 34 degrees and 14 degrees respectively at the same on-design NPR. The lower jet deflection angles observed for sheared exhaust velocity jets is inconsistent with the CWJ model prediction of reduced adverse streamwise pressure gradients; however, there was insufficient experimental instrumentation to identify the cause. In the off-design experiments, the uniform exhaust velocity CWJ was observed to detach at an NPR of 3.6, whilst the sheared exhaust velocity CWJ remained attached at NPRs in excess of 4. The capability of sheared exhaust velocity CWJs to remain attached at higher NPRs is consistent with the analytical theory and the CWJ model predictions. An actuation study was carried out to achieve controlled jet detachment using secondary blowing injected normal to the curved wall. Full separation of the wall jets was achieved downstream of the injection point. This provided vectoring angles of more than 20 degrees in pitch and 10 degrees in yaw, exceeding expected vectoring requirements for practical aircraft control. At the on-design NPR, the uniform and sheared exhaust velocity jets required secondary blowing mass flow rates of 2.1% and 3.8% of the primary mass flow respectively to achieve full separation.

Orientador: Edevar Luvizotto Junior / Dissertação (mestrado) - Universidade Estadual de Campinas, Faculdade de Engenharia Civil, Arquitetura e Urbanismo / Made available in DSpace on 2018-08-07T09:53:33Z (GMT). No. of bitstreams: 1 ArandaSaldana_EdwinAntonio_M.pdf: 1687985 bytes, checksum: 0c5e968a32c41fdf3cc83eca866e6ea6 (MD5) Previous issue date: 2006 / Resumo: O presente trabalho apresenta as bases para a elaboração de um modelo hidráulico computacional baseado na filosofia de programação orientada por objetos (POO) para o tratamento de problemas de escoamento de fluidos em condutos forçados em regime permanente e transitório. Na modelação hidráulica foi empregado um modelo dinâmico inercial elástico com solução através do Método das Características (MOC). Os estudos de casos apresentados mostram o potencial da ferramenta proposta para a análise de escoamentos de instalações hidráulicas em condutos forçados / Abstract: The present work shows the basis for the elaboration of a computational hydraulic model based on the object oriented programming (POO) philosophy for the management of flow problems such as flow rate in pipe systems in steady and unsteady states. The hydraulic modeling is based on the inertial dynamic model with solved through the Method of Characteristics (MOC). The different cases of studies presented in this dissertation show the potential of this tool proposal for the analysis of pipe flow installations in hydraulic systems / Mestrado / Recursos Hidricos / Mestre em Engenharia Civil

This dissertation presents an investigation of the effects of stress, and of absolute and relative particle size, in tests on vertically loaded footings. Two granular materials, namely, a silica rock flour and a Chatelet flint grit, which differed in nominal diameter by a factor of 50 but were otherwise practically similar in all other grain characteristics were used in this work. A comprehensive series of triaxial tests under a wide range of cell pressures was carried out to quantify the stress and absolute particle size effects. Model footing tests were also performed by pushing a rigid circular punch axisymmetrically into the flat surface of a cylindrical soil model either under 1-g (gravity) with surcharge or under elevated g in a centrifuge. The 1-g and centrifuge test series were used to study the scale effects on the surcharge term Ng and the self-weight term Nγ of the Terzaghi bearing capacity equation, respectively. Parameters varied were punch diameter, particle size and surcharge or g level. Two theoretical analyses were attempted based on the finite element method and the method of characteristics. Using the Schofield Soil Model, the finite element analysis can give a reasonable order of magnitude prediction for the settlement of the footing under working load conditions. When the effect of reducing angle of shearing with increasing stress was taken into account together with the change of geometry due to footing penetration, the angles of shearing inferred from the method of characteristics fall within ±20 of those measured in triaxial compression tests. Distortion due to violating the scaling law by not conserving the ratio of particle size to model dimension was not considered to be significant. Distortion due to violating the constitutive soil behaviour by varying the absolute particle size was found to be significant due to differences in grain crushing, but this can be accounted for effectively by the new style of calculations developed in the thesis.

The thesis deals with aerodynamic characteristics identification from flight measurement. The topic is part of flight mechanic – handling qualities. The first theoretic part consists of three identification methods description: Error equation method, Output error method and Filter error method. Mathematical model of an airplane is defined and restricted to the motion with 3 degree of freedom. There is also introduced simulation of flight measurement for identification software validation. Practical part is focused on experiment preparation, execution and evaluation. The airplane VUT 700 Specto had been chosen to carry out flight tests. The airplane was modified to the new electric powered VUT 700e Specto after first measurement flights with combustion engine. Data record from on-board measurement unit was completed by telemetric data from autopilot and remote control system. Flight tests were carried out in stabilised mode of autopilot in symmetric flight. The results were confronted with analytical analysis results and DATCOM+ software parameter estimation.

The thesis deals with aerodynamic characteristics identification from flight measurement. The topic is part of flight mechanic – handling qualities. The first theoretic part consists of three identification methods description: Error equation method, Output error method and Filter error method. Mathematical model of an airplane is defined and restricted to the motion with 3 degree of freedom. There is also introduced simulation of flight measurement for identification software validation. Practical part is focused on experiment preparation, execution and evaluation. The airplane VUT 700 Specto had been chosen to carry out flight tests. The airplane was modified to the new electric powered VUT 700e Specto after first measurement flights with combustion engine. Data record from on-board measurement unit was completed by telemetric data from autopilot and remote control system. Flight tests were carried out in stabilised mode of autopilot in symmetric flight. The results were confronted with analytical analysis results and DATCOM+ software parameter estimation.

Background: This study discusses the phenomenon of luxury goods as investment assets,focusing on luxury watches in particular. The rise of globalization and increased wealth,particularly among the middle and high-income groups in developing countries, hascreated a larger potential customer base for luxury items. This has led to an increasing interest in luxury goods as investment assets, including collectibles such as cars, art, andwine. The recent development of online niche marketplaces for luxury goods has enabledthe systematic collection of data, facilitating research on Veblen goods as alternativeinvestment assets. Therefore, it is interesting to analyze the financial performance ofinvestments in luxury watches as compared to traditional assets. Purpose: The purpose of this study is to analyze the comparative performance ofinvesting in luxury watches versus traditional assets such as equities and bonds. Methodology: This study collects data on luxury watch prices and characteristics. Thehedonic pricing method is used to regress the price of the watches on their characteristics.The regression results are used to analyze the price impact of the characteristics, as well asto create a watch price index. In order to evaluate the index performance, data is collectedfor the MSCI World Index and the Bloomberg U.S. Aggregate Bond Index. For all the indices, the financial metrics of the Sharpe ratio, Treynor ratio, CAPM, and Jensen’s alphaare calculated. Conclusion: This study suggests that luxury watches, with their wide price ranges and high resale value, have been a viable option for portfolio diversification during thestudied five-year period between 2018 and 2023. The watch index yields an averagereturn of 2.01 % and a cumulative return of 49.35 %, outperforming the MSCI World Indexwith average returns of 1.38 % and the Bloomberg U.S. Aggregate Bond Index with -0.01%, and cumulative returns of 31.90 % and -0.15 %, respectively. The watch index alsooutperforms the compared indices in terms of the financial metrics Sharpe ratio, Treynorratio, CAPM, and Jensen’s alpha. The results suggest that the most important valuedrivers for luxury watches are: Brand (Audemars Piguet, Patek Philippe, and VacheronConstantin), Features (Chronograph, tourbillon, and rotating bezel) and Case Material(bronze, rose gold, and yellow gold).