Resumo: Este trabalho apresenta resultados da simulação numérica de escoamentos hipersônicos de fluidos, por meio de pySolver - um aplicativo computacional desenvolvido pelo autor. No aplicativo, as Equações de Euler foram discretizadas pelo método de elementos finitos de Galerkin (GFEM- Galerkin Finite Element Method) juntamente com a técnica CBS (Characteristic Based Split). O aplicativo pySolver, que foi construído baseado nas ferramentas de códigos fontes abertos Python, Blender e Visit, além da linguagem C, possui interface gráfica para o usuário, é multiplataforma e com orientação a objetos, além de contar com um framework especialmente projetado para a realização de todo o pré processamento, visando o modelamento geométrico bi ou tridimensional de problemas. O autor implementou um método para o refinamento de malha, modificando os programas abertos Triangle e TetGen, de tal forma a permitir o refinamento dinâmico e local de malhas até que determinadas tolerâncias sejam alcançadas nos resultados. Isto contribuiu para uma considerável robustez do aplicativo. Para verificação do aplicativo, foram simulados alguns casos-teste de escoamentos supersônicos e hipersônicos ao redor de corpo de diferentes configurações geométricas, principalmente aqueles encontrados na indústria aeronáutica e aeroespacial. Os dados obtidos são comparados com alguns resultados experimentais disponíveis na literatura, quando possível, e também com outros resultados numéricos obtidos da literatura. / Abstract: This work presents some results for the numerical simulation of hypersonic fluid flows, utilizing pySolver - a software developed by the author. In this application, the Euler equations have been discretized by means of the Galerkin Finite Element Method (GFEM) using the CBS (Characteristic Based Split) scheme. pySolver, a multiplatform object-oriented software, built around the set of open source tools Python, Blender and Visit, besides C language, exhibits a proper graphical user interface and a framework specially developed to deal with data pre-processing and capable of geometrical modeling of either two or three-dimensional problems. The author has also implemented a scheme for the mesh refinement, by adapting the open-source softwares Triangle and TetGen, obtaining local and dynamic mesh refinement until reaching a determined tolerance in the results. That refinement scheme has contributed to considerable application robustness. In order to compare the software, some test cases composed of supersonic and hypersonic flows over di erent geometrical configuration bodies, mostly encountered in the aerospace and aeronautic industry data, have been simulated. The results compared very well with experimental data from the literature and, when possible, with other numerical results also obtained in the literature. / Orientador: João Batista Campos Silva / Coorientador: Emanuel Rocha Woiski / Banca: João Batista Aparecido / Banca: Paulo Gilberto de Paula Toro / Mestre

Evaluating aerodynamic noise from aircraft engines is a design stage process, so that it conform to regulations at airports. Aerodynamic noise is also a principal source of structural vibration and internal noise in short/vertical take off and landing and rocket launches. Acoustic loads may be critical for the proper functioning of electronic and mechanical components. It is imperative to have tools with capability to predict noise generation from turbulent flows. Understanding the mechanism of noise generation is essential in identifying methods for noise reduction. Lighthill (1952) and Lighthill (1954) provided the first explanation for the mechanism of aerodynamic noise generation and a procedure to estimate the radiated sound field. Many such procedures, known as acoustic analogies are used for estimating the radiated sound field in terms of the turbulent fluid flow properties. In these methods, the governing equations of the fluid flow are rearranged into two parts, the acoustic sources and the propagation terms. The noise source terms and propagation terms are different in different approaches. A good description of the turbulent flow field and the noise sources is required to understand the mechanism of noise generation. Computational aeroacoustics (CAA) tools are used to calculate the radiated far field noise. The inputs to the CAA tools are results from CFD simulations which provide details of the turbulent flow field and noise sources. Reynolds-Averaged Navier Stokes (RANS) solutions can be used as inputs to CAA tools which require only time-averaged mean quantities. The output of such tools will also be mean quantities. While complete unsteady turbulent flow details can be obtained from Direct Numerical Simulation (DNS), the computation is limited to low or moderate Reynolds number flows. Large eddy simulations (LES) provide accurate description for the dynamics of a range of large scales. Most of the kinetic energy in a turbulent flow is accounted by the large-scale structures. It is also the large-scale structures which accounts for the maximum contribution towards the radiated sound field. The results from LES can be used as an input to a suitable CAA tool to calculate the sound field. Numerical prediction of turbulent flow field, the acoustic sources and the radiated sound field is at the focus of this study. LES based on explicit filtering method is used for the simulations. The method uses a low-pass compact filter to account for the sub-grid scale effects. A one-parameter fourth-order compact filter scheme from Lele (1992) is used for this purpose. LES has been carried out for four different flow situations: (i) round jet (ii) plane jet (iii) impinging round jet and (iv) impinging plane jet. LES has been used to calculate the unsteady flow evolution of these cases and the Lighthill’s acoustic sources. A compact difference scheme proposed by Hixon & Turkel (1998) which involves only bi-diagonal matrices are used for evaluating spatial derivatives. The scheme provides similar spectral resolution as standard tridiagonal compact schemes for the first spatial derivatives. The scheme is computationally less intensive as it involves only bi-diagonal matrices. Also, the scheme employs only a two-point stencil. To calculate the radiated sound field, the Helmholtz equation is solved using the Green’s function approach, in the form of the Kirchhoff-Helmholtz integral. The integral is performed over a surface which is present entirely in the linear region and covers the volume where acoustic sources are present. The time series data of pressure and the normal component of the pressure gradient on the surface are obtained from the CFD results. The Fourier transforms of the time series of pressure and pressure gradient are then calculated and are used as input for the Kirchhoff-Helmholtz integral. The flow evolution for free jets is characterised by the growth of the instability waves in the shear layer which then rolls up into large vortices. These large vortical structures then break down into smaller ones in a cascade which are convected downstream with the flow. The rms values of the Lighthill’s acoustic sources showed that the sources are located mainly at regions immediately downstream of jet break down. This corresponds to the large scale structures at break down. The radiated sound field from free jets contains two components of noise from the large scales and from the small scales. The large structures are the dominant source for the radiated sound field. The contribution from the large structures is directional, mainly at small angles to the downstream direction. To account for the difference in jet core length, the far field SPL are calculated at points suitably shifted based on the jet core length. The peak value for the radiated sound field occurs between 30°and 35°as reported in literature. Convection of acoustic sources causes the radiated sound field to be altered due to Doppler effect. Lighthills sources along the shear layer were examined in the form of (x, t) plots and phase velocity pattern in (ω, k) plots to analyse for their convective speeds. These revealed that there is no unique convective speeds for the acoustic sources. The median convective velocity Uc of the acoustic sources in the shear layer is proportional to the jet velocity Uj at the center of the nozzle as Uc ≈ 0.6Uj. Simulations of the round jet at Mach number 0.9 were used for validating the LES approach. Five different cases of the round jet were used to understand the effect of Reynolds number and inflow perturbation on the flow, acoustic sources and the radiated sound field. Simulations were carried out for an Euler and LES at Reynolds number 3600 and 88000 at two different inflow perturbations. The LES results for the mean flow field, turbulence profiles and SPL directivity were compared with DNS of Freund (2001) and experimental data available in literature. The LES results showed that an increase in inflow forcing and higher Reynolds number caused the jet core length to reduce. The turbulent energy spectra showed that the energy content in smaller scale is higher for higher Reynolds number. LES of plane jets were carried out for two different cases, one with a co-flow and one without co-flow. LES of plane jets were carried out to understand the effect of co-flow on the sound field. The plane jets were of Mach number 0.5 and Reynolds number of 3000 based on center-line velocity excess at the nozzle. This is similar to the DNS by Stanley et al. (2002). It was identified that the co-flow leads to a reduction in turbulence levels. This was also corroborated by the turbulent energy spectrum plots. The far field radiation for the case without co-flow is higher over all angles. The contribution from the low frequencies is directional, mainly towards the downstream direction. The range of dominant convective velocities of the acoustic sources were different along shear layers and center-line. The plane jet results were also used to bring out a qualitative comparison of flow and the radiation characteristics with round jets. For the round jet, the center-line velocity decays linearly with the stream-wise distance. In the plane jet case, it is the square of the center-line velocity excess which decays linearly with the stream-wise distance. The turbulence levels at any section scales with the center-line stream-wise velocity. The decay of turbulence level is slower for the plane jet and hence the acoustic sources are present for longer distance along the downstream direction. Subsonic impinging jets are composed of four regions, the jet core, the fully developed jet, the impingement zone and the wall jet. The presence of the second region (fully developed free jet) depends on the distance of the wall from the nozzle and the length of the jet core. In impinging jets, reflection from the wall and the wall jet are additional sources of noise compared to the free jets. The results are analysed for the contribution of the different regions of the flow towards the radiated sound field. LES simulations of impinging round jets and impinging plane jet were carried out for this purpose. In addition, the results have been compared with equivalent free jets. The directivity plots showed that the SPL levels are significantly higher for the impinging jets at all angles. For free jets, a typical time scale for the acoustic sources is the ratio of the nozzle size to the jet velocity. This is ro/Uj for round jets and h/Uj for plane jets. For impinging jets, the non-dimensionlised rms of Lighthill’s source indicates that the time scale for acoustic sources is the ratio of the height of the nozzle from the wall to the jet velocity be L/Uj. LES of impinging round jets was carried out for two cases with different inflow perturbations. The jets were at Reynolds number of 88000 and Mach number of 0.9, same as the free jet cases. The impingement wall was at a distance L = 24ro from the nozzle exit. For impinging round jets, the SPL levels are found to be higher than the equivalent free jets. From the SPL levels and radiated noise spectra it was shown that the contribution from the large scale structures and its reflection from the wall is directional and at small angles to the wall normal. The difference in the range of angles where the radiation from the large scale structures were observed shows the significance of refraction of sound waves inside the flow. The rms values of the Lighthill’s sources indicate two dominant regions for the sources, just downstream of jet breakdown and in the impingement zone. The LES of impinging plane jet was done for a jet of Mach number 0.5 and Reynolds number of 6000. The impingement wall was at a distance L = 10h from the nozzle exit. The radiated sound field appears to emanate from this impingement zone. The directivity and the spectrum plots of the far field SPL indicate that there is no preferred direction of radiation from the impingement zone. The Lighthill’s sources are concentrated mainly in the impingement zone. The rms values of the sources indicate that the peak values occur in the impingement zone. The results from the different flow situations demonstrates the capability of LES with explicit filtering method in predicting the turbulent flow and radiated noise field. The method is robust and has been successfully used for moderate Reynolds number and an Euler simulation. An important feature is that LES can be used to identify acoustic sources and its convective speeds. It has been shown that the Lighthill source calculations, the calculated sound field and the observed radiation patterns agree well. An explanation for these based on the different turbulent flow structures has also been provided.

In the last half a century, Computational Fluid Dynamics (CFD) has been established as an important complementary part and some times a significant alternative to Experimental and Theoretical Fluid Dynamics. Development of efficient computational algorithms for digital simulation of fluid flows has been an ongoing research effort in CFD. An accurate numerical simulation of compressible Euler equations, which are the gov-erning equations of high speed flows, is important in many engineering applications like designing of aerospace vehicles and their components. Due to nonlinear nature of governing equations, such flows admit solutions involving discontinuities like shock waves and contact discontinuities. Hence, it is nontrivial to capture all these essential features of the flows numerically. There are various numerical methods available in the literature, the popular ones among them being the Finite Volume Method (FVM), Finite Difference Method (FDM), Finite Element Method (FEM) and Spectral method. Kinetic theory based algorithms for solving Euler equations are quite popular in finite volume framework due to their ability to connect Boltzmann equation with Euler equations. In kinetic framework, instead of dealing directly with nonlinear partial differential equations one needs to deal with a simple linear partial differential equation. Recently, FEM has emerged as a significant alternative to FVM because it can handle complex geometries with ease and unlike in FVM, achieving higher order accuracy is easier. High speed flows governed by compressible Euler equations are hyperbolic partial differential equations which are characterized by preferred directions for information propagation. Such flows can not be solved using traditional FEM methods and hence, stabilized methods are typically introduced. Various stabilized finite element methods are available in the literature like Streamlined-Upwind Petrov Galerkin (SUPG) method, Galerkin-Least Squares (GLS) method, Taylor-Galerkin method, Characteristic Galerkin method and Discontinuous Galerkin Method. In this thesis a novel stabilized finite element method called as Kinetic Streamlined-Upwind Petrov Galerkin (KSUPG) method is formulated. Both explicit and implicit versions of KSUPG scheme are presented. Spectral stability analysis is done for explicit KSUPG scheme to obtain the stable time step. The advantage of proposed scheme is, unlike in SUPG scheme, diffusion vectors are obtained directly from weak KSUPG formulation. The expression for intrinsic time scale is directly obtained in KSUPG framework. The accuracy and robustness of the proposed scheme is demonstrated by solving various test cases for hyperbolic partial differential equations like Euler equations and inviscid Burgers equation. In the KSUPG scheme, diffusion terms involve computationally expensive error and exponential functions. To decrease the computational cost, two variants of KSUPG scheme, namely, Peculiar Velocity based KSUPG (PV-KSUPG) scheme and Circular distribution based KSUPG (C-KSUPG) scheme are formulated. The PV-KSUPG scheme is based on peculiar velocity based splitting which, upon taking moments, recovers a convection-pressure splitting type algorithm at the macroscopic level. Both explicit and implicit versions of PV-KSUPG scheme are presented. Unlike KSUPG and PV-KUPG schemes where Maxwellian distribution function is used, the C-KUSPG scheme uses a simpler circular distribution function instead of a Maxwellian distribution function. Apart from being computationally less expensive it is less diffusive than KSUPG scheme.

Cette thèse est consacrée à l'étude théorique de quelques modèles d'évolution non-linéaires issus de la mécanique des fluides. Nous distinguons trois parties indépendantes. La première partie de la thèse traite essentiellement de l'existence des poches de tourbillon en rotation uniforme (appelées aussi V-states) pour un modèle quasi-géostrophique non visqueux. Notre étude est répartie sur deux chapitres où les poches présentent des structures topologiques différentes. Dans le premier chapitre nous étudions le cas simplement connexe et nous validons l'existence de ces structures dans un voisinage du tourbillon de Rankine en utilisant des techniques de bifurcation. Dans le deuxième chapitre nous abordons le cas doublement connexe où la poche admet un seul trou. Plus précisément, proche d'un anneau donné, nous décrivons cette famille par des branches dénombrables bifurquant de cet anneau à certaines valeurs explicites des vitesses angulaires liées aux fonctions de Bessel. Notre étude théorique a été complétée par des simulations numériques portant sur les V-states limites et un bon nombre de constatations ont été formulées ouvrant la porte à de nouvelles perspectives de recherche. La seconde partie concerne l'étude du problème de Cauchy pour le système de Boussinesq non visqueux 2D avec des données initiales de type Yudovich. Le problème est dans un certain sens critique à cause de quelques termes comportant la transformée de Riesz dans la formulation tourbillon-densité. Nous donnons une réponse positive pour une sous-classe comprenant les poches de tourbillon régulières et singulières. Dans la dernière partie nous analysons le problème de la limite incompressible pour les équations d'Euler isentropiques 2D associées à des données initiales très mal préparées et pour lesquelles les tourbillons ne sont pas forcément bornés mais appartiennent plutôt à des espaces de type ''BMO'' à poids. On utilise principalement deux ingrédients: d'un côté les estimations de Strichartz pour contrôler la partie acoustique. D'un autre côté, on se sert de la structure de transport compressible du tourbillon et on démontre une estimation de propagation linéaire dans l'esprit d'un travail récent de Bernicot et Keraani mené dans le cas incompressible. / In this dissertation, we are concerned with the study of some non-linear evolution models arising in fluid mechanics. We distinguish three independent parts. The first part of the thesis deals with the existence of the rotating vortex patches (called also V-states) for an inviscid quasi-geostrophic model. Our study is divided into two chapters dealing with different topological structures of the V-states. In the first chapter we study the simply connected case and we prove the existence of such structures in a neighborhood of the Rankine vortices by using the bifurcation theory. In the second chapter we discuss the doubly connected case where the patches admit only one hole. More precisely, close to a given annulus we describe this family by countable branches bifurcating from this annulus at some explicit angular velocities related to Bessel functions of the first kind. Our theoretical study was completed by numerical simulations on the limiting V-states and a number of interesting numerical observation were formulated opening new research perspectives. The second part of the thesis concerns the local well-posedness theory for the inviscid Boussinesq system with rough initial data. The problem is in some sense critical due to some terms involving Riesz transforms in the vorticity-density formulation. We give a positive answer for a special sub-class of Yudovich data including smooth and singular vortex patches. In the last part we address the problem of the incompressible limit for the 2D isentropic fluids associated to ill-prepared initial data and for which the vortices are not necessarily bounded and belong to some weighted BMO spaces. We mainly use two ingredients: On one hand, the Strichartz estimates to control the acoustic part and prove that it does not contribute for low Mach number. On the other hand, we use the transport compressible structure of the vorticity and we establish a linear propagation estimate in the spirit of a recent work of Bernicot and Keraani conducted in the incompressible case. The first part of the thesis deals with the existence of the rotating vortex patches (called also V-states) for an inviscid quasi-geostrophic model. Our study is divided into two chapters dealing with different topological structures of the V-states. In the first chapter we study the simply connected case and we prove the existence of such structures in a neighborhood of the Rankine vortices by using the bifurcation theory. In the second chapter we discuss the doubly connected case where the patches admit only one hole. More precisely, close to a given annulus we describe this family by countable branches bifurcating from this annulus at some explicit angular velocities related to Bessel functions of the first kind. Our theoretical study was completed by numerical simulations on the limiting V-states and a number of interesting numerical observation were formulated opening new research perspectives. The second part of the thesis concerns the local well-posedness theory for the inviscid Boussinesq system with rough initial data. The problem is in some sense critical due to some terms involving Riesz transforms in the vorticity-density formulation. We give a positive answer for a special sub-class of Yudovich data including smooth and singular vortex patches. In the last part we address the problem of the incompressible limit for the 2D isentropic fluids associated to ill-prepared initial data and for which the vortices are not necessarily bounded and belong to some weighted BMO spaces. We mainly use two ingredients: On one hand, the Strichartz estimates to control the acoustic part and prove that it does not contribute for low Mach number. On the other hand, we use the transport compressible structure of the vorticity and we establish a linear propagation estimate in the spirit of a recent work of Bernicot and Keraani conducted in the incompressible case.

This work makes basic analysis of historical and current algorithms for smoke animation. Modern approaches to rendering volumetric data are briefly described. We choose algorithms for implementation on basis of this analysis. These algorithms are described in detail and we make emphasis on their important properties according to dedication of this work. Detailed description of implementation follows along with performance measurement. Conclusion evaluates results of work and proposes possible extensions.

This work develops a discontinuous Galerkin finite element discretization of non- linear hyperbolic conservation equations with efficient and robust high order stabilization built on an entropy-based artificial viscosity approximation. The solutions of equations are represented by elementwise polynomials of an arbitrary degree p > 0 which are continuous within each element but discontinuous on the boundaries. The discretization of equations in time is done by means of high order explicit Runge-Kutta methods identified with respective Butcher tableaux. To stabilize a numerical solution in the vicinity of shock waves and simultaneously preserve the smooth parts from smearing, we add some reasonable amount of artificial viscosity in accordance with the physical principle of entropy production in the interior of shock waves. The viscosity coefficient is proportional to the local size of the residual of an entropy equation and is bounded from above by the first-order artificial viscosity defined by a local wave speed. Since the residual of an entropy equation is supposed to be vanishingly small in smooth regions (of the order of the Local Truncation Error) and arbitrarily large in shocks, the entropy viscosity is almost zero everywhere except the shocks, where it reaches the first-order upper bound. One- and two-dimensional benchmark test cases are presented for nonlinear hyperbolic scalar conservation laws and the system of compressible Euler equations. These tests demonstrate the satisfactory stability properties of the method and optimal convergence rates as well. All numerical solutions to the test problems agree well with the reference solutions found in the literature. We conclude that the new method developed in the present work is a valuable alternative to currently existing techniques of viscous stabilization.

La simulation numérique est aujourd'hui un outils majeur dans la conception des objets aérodynamiques, que ce soit dans l'aéronautique, l'automobile, l'industrie navale, etc... Un des défis majeurs pour repousser les limites des codes de simulation est d'améliorer leur précision, tout en utilisant une quantité fixe de ressources (puissance et/ou temps de calcul). Cet objectif peut être atteint par deux approches différentes, soit en construisant une discrétisation fournissant sur un maillage donné une solution d'ordre très élevé, soit en construisant un schéma compact et massivement parallèlisable, de manière à minimiser le temps de calcul en distribuant le problème sur un grand nombre de processeurs. Dans cette thèse, nous tentons de rassembler ces deux approches par le développement et l'implémentation de Schéma Distribuant le Résidu (RDS) d'ordre très élevé et de compacité maximale. Ce manuscrit commence par un rappel des principaux résultats mathématiques concernant les Lois de Conservation hyperboliques (CLs). Le but de cette première partie est de mettre en évidence les propriétés des solutions analytiques que nous cherchons à approcher, de manière à injecter ces propriétés dans celles de la solution discrète recherchée. Nous décrivons ensuite les trois étapes principales de la construction d'un schéma RD d'ordre très élevé : - la représentation polynomiale d'ordre très élevé de la solution sur des polygones et des polyèdres; - la description de méthodes distribuant le résidu de faible ordre, compactes et conservatives, consistantes avec une représentation polynomiale des données de très haut degré. Parmi elles, une attention particulière est donnée à la plus simple, issue d'une généralisation du schéma de Lax-Friedrichs (\LxF); - la mise en place d'une procédure préservant la positivité qui transforme tout schéma stable et linéaire, en un schéma non linéaire d'ordre très élevé, capturant les chocs de manière non oscillante. Dans le manuscrit, nous montrons que les schémas obtenus par cette procédure sont consistants avec la CL considérée, qu'ils sont stables en norme $\L^{\infty}$ et qu'ils ont la bonne erreur de troncature. Même si tous ces développements théoriques ne sont démontrés que dans le cas de CLs scalaires, des remarques au sujet des problèmes vectoriels sont faites dès que cela est possible. Malheureusement, lorsqu'on considère le schéma \LxF, le problème algébrique non linéaire associé à la recherche de la solution stationnaire est en général mal posé. En particulier, on observe l'apparition de modes parasites de haute fréquence dans les régions de faible gradient. Ceux-ci sont éliminés grâce à un terme supplémentaire de stabilisation dont les effets et l'évaluation numérique sont précisément détaillés. Enfin, nous nous intéressons à une discrétisation correcte des conditions limites pour le schéma d'ordre élevé proposé. Cette théorie est ensuite illustrée sur des cas test scalaires bidimensionnels simples. Afin de montrer la généralité de notre approche, des maillages composés uniquement de triangles et des maillages hybrides, composés de triangles et de quandrangles, sont utilisés. Les résultats obtenus par ces tests confirment ce qui est attendu par la théorie et mettent en avant certains avantages des maillages hybrides. Nous considérons ensuite des solutions bidimensionnelles des équations d'Euler de la dynamique des gaz. Les résultats sont assez bons, mais on perd les pentes de convergence attendues dès que des conditions limite de paroi sont utilisées. Ce problème nécessite encore d'être étudié. Nous présentons alors l'implémentation parallèle du schéma. Celle-ci est analysée et illustrée à travers des cas test tridimensionnel de grande taille. / Numerical simulations are nowadays a major tool in aerodynamic design in aeronautic, automotive, naval industry etc... One of the main challenges to push further the limits of the simulation codes is to increase their accuracy within a fixed set of resources (computational power and/or time). Two possible approaches to deal with this issue are either to contruct discretizations yielding, on a given mesh, very high order accurate solutions, or to construct compact, massively parallelizable schemes to minimize the computational time by means of a high performance parallel implementation. In this thesis, we try to combine both approaches by investigating the contruction and implementation of very high order Residual Distribution Schemes (RDS) with the most possible compact stencil. The manuscript starts with a review of the mathematical theory of hyperbolic Conservation Laws (CLs). The aim of this initial part is to highlight the properties of the analytical solutions we are trying to approximate, in order to be able to link these properties with the ones of the sought discrete solutions. Next, we describe the three main steps toward the construction of a very high order RDS: - The definition of higher order polynomial representations of the solution over polygons and polyhedra; - The design of low order compact conservative RD schemes consistent with a given (high degree) polynomial representation. Among these, particular accest is put on the simplest, given by a generalization of the Lax-Friedrich's (\LxF) scheme; - The design of a positivity preserving nonlinear transformation, mapping first-order linear schemes onto nonlinear very high order schemes. In the manuscript, we show formally that the schemes obtained following this procedure are consistent with the initial CL, that they are stable in $L^{\infty}$ norm, and that they have the proper truncation error. Even though all the theoretical developments are carried out for scalar CLs, remarks on the extension to systems are given whenever possible. Unortunately, when employing the first order \LxF scheme as a basis for the construction of the nonlinear discretization, the final nonlinear algebraic equation is not well-posed in general. In particular, for smoothly varying solutions one observes the appearance of high frequency spurious modes. In order to kill these modes, a streamline dissipation term is added to the scheme. The analytical implications of this modifications, as well as its practical computation, are thouroughly studied. Lastly, we focus on a correct discretization of the boundary conditions for the very high order RDS proposed. The theory is then extensively verified on a variety of scalar two dimensional test cases. Both triangular, and hybrid triangular-quadrilateral meshes are used to show the generality of the approach. The results obtained in these tests confirm all the theoretical expectations in terms of accuracy and stability and underline some advantages of the hybrid grids. Next, we consider solutions of the two dimensional Euler equations of gas dynamics. The results obtained are quite satisfactory and yet, we are not able to obtain the desired convergence rates on problems involving solid wall boundaries. Further investigation of this problem is under way. We then discuss the parallel implementation of the schemes, and analyze and illustrate the performance of this implementation on large three dimensional problems. Due to the preliminary character and the complexity of these three dimensional problems, a rather qualitative discussion is made for these tests cases: the overall behavior seems to be the correct one, but more work is necessary to assess the properties of the schemes in three dimensions.

Cette thèse s'inscrit dans l'étude des modèles asymptotiques aux équations des ondes de surface dans le régime modulationnel. Le problème des ondes de surface consiste à décrire le mouvement - sous l'influence de la gravitation et éventuellement de tension de surface - d'un fluide dans un domaine délimité par la surface libre du fluide et par un fond fixe. Dans l'étude de ce problème, on s'intéresse en particulier aux ondes se propageant à la surface du fluide.Dans le régime modulationnel, on considère l'évolution des ondes de surface sous forme de paquets d'ondes de faible amplitude se propageant dans une direction. Il est bien connu que la motion de l'enveloppe du paquet d'onde sur une échelle de temps d'ordre t = O(1/ϵ²), où ϵ est un petit paramètre désignant l'amplitude, est décrite approximativement par des systèmes d'équations appelés systèmes de Benney-Roskes (BR) / Davey-Stewartson (DS). Ces systèmes sont donnés par une équation de type Schrödinger cubique couplée à une équation d'ondes. L'approximation classique de BR / DS est bien établie et a été largement étudiée au cours des dernières décennies. Récemment, David Lannes a introduit une version à "dispersion exacte" de ces systèmes. Contrairement aux équations de BR / DS standard, les systèmes à dispersion exacte préservent la relation de dispersion des équations des ondes de surface. On devrait obtenir ainsi une description plus riche du vrai comportement dynamique des ondes de surface que dans le cas de l'approximation classique.Le systèmes de BR / DS à dispersion exacte sont étudiés dans cette thèse. La première partie est consacrée à la déduction formelle des systèmes de BR / DS en tant que modèles asymptotiques aux équations des ondes de surface. Nous donnons en outre un résultat sur la consistance de cette approximation.Ensuite, nous étudions le problème de Cauchy pour le système de BR à dispersion exacte. En fait, afin de justifier la consistance de l'approximation de BR avec les équations exactes, on doit prouver que ce système est bien posé (en espace de Sobolev) sur une échelle de temps d'ordre O(1/ϵ). Ceci est un problème ouvert même dans le cas classique, du moins pour le système de dimension 1 + 2. De même, nous ne pouvons pas démontrer l'existence de solutions en temps long pour le système de BR à dispersion exacte, mais nous obtenons un théorème d'existence locale (t = O(1)) à condition que la tension de surface soit assez forte. Si nous nous restreignons au système de dimension 1+1, nous pouvons enlever la contrainte sur la tension de surface. L'idée de la preuve d'existence locale, qui est inspirée par un travail de Schochet-Weinstein, est d'écrire le système de BR comme un système symétrique hyperbolique quasi-linéaire perturbé par un terme dispersif ne contribuant pas à l'énergie du système. Ainsi, nous pouvons appliquer les méthodes standard de résolution des systèmes hyperboliques.En modifiant le terme non-linéaire du système de BR de dimension 1+1 sans changer l'ordre de consistance, nous obtenons un système qui est bien posé sur l'échelle de temps appropriée O(1/ϵ). Cependant, cette démarche ne peut pas être généralisée au cas de dimension 1+2.Dans le dernier chapitre de cette thèse, nous donnons quelques résultats sur les systèmes de Davey-Stewartson à dispersion exacte. Pour les systèmes de DS, il est suffisant de démontrer qu'ils sont bien posés localement afin de justifier leur consistance avec les équations des ondes de surface. La théorie d'existence de solutions est assez complète pour le système de DS classique. Dans le cas de dispersion exacte cependant, les équations paraissent mal posées généralement, si bien que l'existence locale ne peut être démontrée pour l'instant que pour quelques cas particuliers simples. / This thesis is concerned with asymptotic models to the water wave equations in the modulational regime. The water wave equations describe the motion - under the influence of gravity and possibly surface tension - of an inviscid fluid in a domain which is bounded by a fixed bottom from below and the free surface of the fluid from above. In the study of the water wave problem, one is in particular interested by waves propagating on the surface of the fluid.In the modulational regime, one considers the evolution of surface waves under the form of small amplitude wave packets traveling in one direction. It is well known that the evolution of the wave packet envelope on the long time scale t = O(1/ϵ²), where ϵ is a small parameter denoting the amplitude of the wave, is approximately governed by a set of equations known as the Benney-Roskes (BR) / Davey-Stewartson (DS) systems. These systems are essentially given by a cubic Schrödinger-type equation coupled to a wave equation. The classical BR / DS approximation is well established and has been largely studied in the past decades. Recently, David Lannes has introduced a "full dispersion" version of these systems. In contrast to the standard BR / DS equations, the full dispersion systems preserve the linear dispersion relation of the full water wave equations, and should therefore give a richer description of the original wave dynamics than the classical approximation.The full dispersion BR / DS systems are studied in this thesis. In the first part, we formally derive the full dispersion BR / DS approximation from the water wave equations both in the case of zero and positive surface tension. The formal derivation is completed by a consistency result.We then study well-posedness in Sobolev space of the full dispersion BR system. In order to justify consistency of the BR approximation with the full water wave equations, one needs to show that the BR system is well posed on a time scale of order O(1/ϵ). This is an open problem even in the classical case, at least for the 1 + 2 dimensional system. We also do not obtain well-posedness on the long time scale for the full dispersion BR system, but we can show that it is locally well-posed in the case of sufficiently strong surface tension, and additionally in the zero surface tension case if we restrict ourselves to the 1+1 dimensional system. The proof is inspired by a paper of Schochet-Weinstein, and is based on writing the full dispersion BR system as a quasilinear symmetric hyperbolic system with dispersive perturbation, where the dispersive terms do not contribute to the energy. We can therefore apply classical solution methods for hyperbolic systems.By modifying the nonlinear part of the 1+1 dimensional full dispersion BR system without changing consistency, we obtain a system that is well-posed on the appropriate O(1/ϵ) time scale. This approach however does not generalize to the 1+2 dimensional case.In the last chapter of the thesis, we give some results on the full dispersion DS systems, which are obtained as special limits of the full dispersion BR system. For these systems, it is sufficient to prove local well-posedness in order to show consistency with the water wave equations. For the standard DS systems, local well-posedness theory is quite complete. For the full dispersion systems, the analysis is complicated by some nonlocal operators and the equations seem to be generally ill-posed. There are however some simple cases where local well-posedness can be shown. We also discuss some modifications of the full dispersion DS system that might allow to solve it for a larger range of parameters.

Cette thèse porte sur le comportement en temps long de solutions d’équations de type Vlasov, principalement le modèle Vlasov-HMF. On s’intéresse en particulier au phénomène d’amortissement Landau, prouvé mathématiquement dans divers cadres, pour plusieurs équations de type Vlasov, comme l’équation de Vlasov-Poisson ou le modèle Vlasov-HMF, et présentant certaines analogies avec le phénomène d’amortissement non visqueux pour l’équation d’Euler 2D. Les résultats qui y sont décrits sont les suivants. Le premier est un théorème d’amortissement Landau pour des solutions numériques du modèle Vlasov-HMF, obtenues par discrétisation en temps de ce dernier via des méthodes de splitting. Nous prouvons en outre la convergence des schémas numériques. Le second est un théorème d’amortissment Landau pour des solutions du modéle Vlasov-HMF linéarisé autour d’états stationnaires inhomogènes. Ce théorème est accompagné de nombreuses simulations numériques destinées à étudier numériquement le cas non-linéaire, et semblant mettre en lumière de nouveaux phénomènes. Enfin, le dernier résultat porte sur la discrétisation en temps de l’équation d’Euler 2D par un intégrateur de Crouch-Grossman symplectique. Nous prouvons la convergence du schéma. / This thesis concerns the long time behavior of certain Vlasov equations, mainly the Vlasov- HMF model. We are in particular interested in the celebrated phenomenon of Landau damp- ing, proved mathematically in various frameworks, foar several Vlasov equations, such as the Vlasov-Poisson equation or the Vlasov-HMF model, and exhibiting certain analogies with the inviscid damping phenomenon for the 2D Euler equation. The results described in the document are the following.The first one is a Landau damping theorem for numerical solutions of the Vlasov-HMF model, constructed by means of time-discretizations by splitting methods. We prove more- over the convergence of the schemes. The second result is a Landau damping theorem for solutions of the Vlasov-HMF model linearized around inhomogeneous stationary states. We provide moreover a quite large amount of numerical simulations, which are designed to study numerically the nonlinear case, and which seem to show new phenomenons. The last result is the convergence of a scheme that discretizes in time the 2D Euler equation by means of a symplectic Crouch-Grossmann integrator.

Lors de simulations numériques d’ordre élevé, la discrétisation sous-paramétrique du domaine de calcul peut générer des erreurs dominant l’erreur liée à la discrétisation des variables. De nombreux travaux proposent d’utiliser l’analyse isogéométrique afin de mieux représenter les géométries et de résoudre ce problème.Nous présenterons dans ce travail le couplage du schéma aux résidus distribués limité et stabilisé de Lax-Frieirichs avec l’analyse isogéométrique. En particulier, nous construirons une famille de fonctions de base permettant de représenter exactement les coniques et définies tant sur les éléments triangulaires que quadrangulaires : les fonctions de base de Bernstein rationnelles. Nous nous intéresserons ensuite à la génération de maillages précis pour l’analyse isogéométrique. Notre méthode consiste à créer un maillage courbe à partir d’un maillage linéaire par morceaux de la géométrie. Le maillage obtenu en sortie de notre procédure est non-structuré, conforme et assure la continuité de nos fonctions de base sur tout le domaine. Pour finir, nous décrirons les différentes méthodes d’adaptation de maillages développées : l’élévation d’ordre et le raffinement isotrope. Bien évidemment, la géométrie exacte du maillage courbe d’entrée est préservée au cours des processus d’adaptation. / During high order simulations, the approximation error may be dominated by the errors linked to the sub-parametric discretization used for the geometry representation. Many works propose to use an isogeometric analysis approach to better represent the geometry and hence solve this problem. In this work, we will present the coupling between the limited stabilized Lax-Friedrichs residual distributed scheme and the isogeometric analysis. Especially, we will build a family of basis functions defined on both triangular and quadrangular elements and allowing the exact representation of conics : the rational Bernstein basis functions. We will then focus in how to generate accurate meshes for isogeometric analysis. Our idea is to create a curved mesh from a classical piecewise-linear mesh of the geometry. We obtain a conforming unstructured mesh which ensures the continuity of the basis functions over the entire mesh. Last, we will detail the curved mesh adaptation methods developed : the order elevation and the isotropic mesh refinement. Of course, the adaptation processes preserve the exact geometry of the initial curved mesh.