Academic literature on the topic 'Upwind scheme'

A multi-dimensional upwind fluctuation splitting scheme is developed and implemented for two-dimensional and axisymmetric formulations of the Navier-Stokes equations on unstructured meshes. Key features of the scheme are the compact stencil, full upwinding, and non-linear discretization which allow for second-order accuracy with enforced positivity. Throughout, the fluctuation splitting scheme is compared to a current state-of-the-art finite volume approach, a second-order, dual mesh upwind flux difference splitting scheme (DMFDSFV), and is shown to produce more accurate results using fewer computer resources for a wide range of test cases. The scalar test cases include advected shear, circular advection, non-linear advection with coalescing shock and expansion fans, and advection-diffusion. For all scalar cases the fluctuation splitting scheme is more accurate, and the primary mechanism for the improved fluctuation splitting performance is shown to be the reduced production of artificial dissipation relative to DMFDSFV. The most significant scalar result is for combined advection-diffusion, where the present fluctuation splitting scheme is able to resolve the physical dissipation from the artificial dissipation on a much coarser mesh than DMFDSFV is able to, allowing order-of-magnitude reductions in solution time. Among the inviscid test cases the converging supersonic streams problem is notable in that the fluctuation splitting scheme exhibits superconvergent third-order spatial accuracy. For the inviscid cases of a supersonic diamond airfoil, supersonic slender cone, and incompressible circular bump the fluctuation splitting drag coefficient errors are typically half the DMFDSFV drag errors. However, for the incompressible inviscid sphere the fluctuation splitting drag error is larger than for DMFDSFV. A Blasius flat plate viscous validation case reveals a more accurate vertical-velocity profile for fluctuation splitting, and the reduced artificial dissipation production is shown relative to DMFDSFV. Remarkably the fluctuation splitting scheme shows grid converged skin friction coefficients with only five points in the boundary layer for this case. A viscous Mach 17.6 (perfect gas) cylinder case demonstrates solution monotonicity and heat transfer capability with the fluctuation splitting scheme. While fluctuation splitting is recommended over DMFDSFV, the difference in performance between the schemes is not so great as to obsolete DMFDSFV. The second half of the dissertation develops a local, compact, anisotropic unstructured mesh adaption scheme in conjunction with the multi-dimensional upwind solver, exhibiting a characteristic alignment behavior for scalar problems. This alignment behavior stands in contrast to the curvature clustering nature of the local, anisotropic unstructured adaption strategy based upon a posteriori error estimation that is used for comparison. The characteristic alignment is most pronounced for linear advection, with reduced improvement seen for the more complex non-linear advection and advection-diffusion cases. The adaption strategy is extended to the two-dimensional and axisymmetric Navier-Stokes equations of motion through the concept of fluctuation minimization. The system test case for the adaption strategy is a sting mounted capsule at Mach-10 wind tunnel conditions, considered in both two-dimensional and axisymmetric configurations. For this complex flowfield the adaption results are disappointing since feature alignment does not emerge from the local operations. Aggressive adaption is shown to result in a loss of robustness for the solver, particularly in the bow shock/stagnation point interaction region. Reducing the adaption strength maintains solution robustness but fails to produce significant improvement in the surface heat transfer predictions.<br>Ph. D.

A new numerical procedure has been developed for the finite-volume solution of the Euler equations on unstructured, triangular meshes using a flux-difference split, upwind method. The procedure uses a dual mesh system to implement the finite-volume scheme using conserved variables stored at the vertices of the triangles. The vertices of the triangles are located approximately in the center of the dual mesh cells and conservation is enforced about each dual mesh finite-volume. Techniques are developed for implementing Roe's approximate Riemann solver on unstructured grids. Higher order accuracy is achieved by using MUSCL-differencing. MUSCL-differencing is implemented on an unstructured grid by interpolating the values stored at the vertices of triangular elements to find the value at the outermost point of the three-point MUSCL-differencing formula. Flow solutions are computed using a four-stage Runge-Kutta time integration. Convergence is accelerated using non-standard weighting of the Runge-Kutta stages, variable time-steps, residual smoothing and residual min- imization. Applications and comparisons with structured grid solutions are made for a supersonic shock reflection problem, the supersonic flow over a blunt body, flow through a simple wedge inlet, and several AGARD 07 working group transonic airfoils. In general, the solutions computed by the upwind solver on the unstructured grids were as accurate as upwind solutions on a structured mesh. The blunt body solution, and some of the transonic airfoil solutions on the unstructured meshes, appeared to be less accurate than the structured mesh solutions. Fortuitously, the structured meshes used in these solutions tended to line up with the shock waves present in the flow-field. The upwind flux-differencing scheme captured the shock wave with greatest accuracy when it was applied normal to the discontinuity, as was done in these test cases.<br>Ph. D.

With increasing demand for computational solutions of fluid dynamical problems, researchers around the world are working on the development of highly robust numerical schemes capable of solving flow problems around complex geometries arising in Aerospace engineering. Also considerable time and effort are devoted to development of convergence acceleration devices, for reducing the computational time required for such numerical solutions. Reduction in run times is very vital for production codes which are used many times in design cycle. In this present work, we consider a numerical scheme called LSKUM capable of operating on any arbitrary distribution of points. LSKUM is being used in CFD center (IIsc) and DRDL (Hyderabad) to compute flows around practical geometries and presently these LSKUM based codes are explicit- It has been observed already by the earlier researchers that the explicit schemes for these methods are robust. Therefore, it is absolutely essential to consider the possibility of accelerating explicit LSKUM by making it LSKUM-Implicit. The present thesis focuses on such a study. We start with two kinetic schemes namely Least Squares Kinetic Upwind Method (LSKUM) and LSKUM based on entropy variables (q-LSKUM). We have developed the following two implicit schemes using LSKUM and q-LSKUM. They are (i)Non-Linear Iterative Implicit Scheme called LSKUM-NII. (ii)Linearized Beam and Warming implicit Scheme, called LSKUM-BW. For the purpose of demonstration of efficiency of the newly developed above implicit schemes, we have considered flow past NACA0012 airfoil as a test example. In this regard we have tested these implicit schemes for flow regimes mentioned below •Subsonic Case: M∞ = 0.63, a.o.a = 2.0° •Transonic Case: M∞ = 0.85, a.o.a = 1.0° The speedup of the above two implicit schemes has been studied in this thesis by operating them on different grid sizes given below •Coarse Grid: 4074 points •Medium Grid: 8088 points •Fine Grid: 16594 points The results obtained by running these implicit schemes are found to be very much encouraging. It has been observed that these newly developed implicit schemes give as much as 2.8 times speedup compared to their corresponding explicit versions. Further improvement is possible by combining LKSUM-Implicit with modern iterative methods of solving resultant algebraic equations. The present work is a first step towards this objective.

With increasing demand for computational solutions of fluid dynamical problems, researchers around the world are working on the development of highly robust numerical schemes capable of solving flow problems around complex geometries arising in Aerospace engineering. Also considerable time and effort are devoted to development of convergence acceleration devices, for reducing the computational time required for such numerical solutions. Reduction in run times is very vital for production codes which are used many times in design cycle. In this present work, we consider a numerical scheme called LSKUM capable of operating on any arbitrary distribution of points. LSKUM is being used in CFD center (IIsc) and DRDL (Hyderabad) to compute flows around practical geometries and presently these LSKUM based codes are explicit- It has been observed already by the earlier researchers that the explicit schemes for these methods are robust. Therefore, it is absolutely essential to consider the possibility of accelerating explicit LSKUM by making it LSKUM-Implicit. The present thesis focuses on such a study. We start with two kinetic schemes namely Least Squares Kinetic Upwind Method (LSKUM) and LSKUM based on entropy variables (q-LSKUM). We have developed the following two implicit schemes using LSKUM and q-LSKUM. They are (i)Non-Linear Iterative Implicit Scheme called LSKUM-NII. (ii)Linearized Beam and Warming implicit Scheme, called LSKUM-BW. For the purpose of demonstration of efficiency of the newly developed above implicit schemes, we have considered flow past NACA0012 airfoil as a test example. In this regard we have tested these implicit schemes for flow regimes mentioned below •Subsonic Case: M∞ = 0.63, a.o.a = 2.0° •Transonic Case: M∞ = 0.85, a.o.a = 1.0° The speedup of the above two implicit schemes has been studied in this thesis by operating them on different grid sizes given below •Coarse Grid: 4074 points •Medium Grid: 8088 points •Fine Grid: 16594 points The results obtained by running these implicit schemes are found to be very much encouraging. It has been observed that these newly developed implicit schemes give as much as 2.8 times speedup compared to their corresponding explicit versions. Further improvement is possible by combining LKSUM-Implicit with modern iterative methods of solving resultant algebraic equations. The present work is a first step towards this objective.

Este trabalho de pesquisa é dedicado ao desenvolvimento, análise e implementação de um novo esquema upwind de alta resolução (denominada PFDPUS) para a aproximação de termos convectivos em leis de conservação e problemas relacionados em mecânica dos fluídos. Usando variáveis normalizadas de Leonard, o equema PFDPUS é baseado em uma função polinomial por partes que satisfaz os critérios de estabilidade CBC e TVD. O desempenho do esquema PEDPUS é investigado na solução das equações de advecção de escalares, Burgers, Euler e MHD. O novo esquema é então aplicado para simular escoamentos incompressíveis envolvendo superfícies livres móveis. Para tanto, o esquema PFDPUS é implementado dentro do software CLAWPACK para problemas compressíveis, e no código Freeflow para poblemas incompressíveis. Os resultados numéricos são comparados com dados experimentais, numéricos e analíticos<br>This work is dedicated to the development, analysis and implementation of a new high-resolution upwind scheme (called PFDPUS) for approximation of convective terms in conservation laws and related fluid mechanics problems. By using the normalized variables of Leonard, the PFDPUS scheme is based on a piecewise polynomical function that satisfies the CBC and TVD stability criteria. The performance of the PFDPUS scheme is assessed by solving advection of scalars, Burgers, Euler and MHD equations. Then the new scheme is applied to simulate incompressible flows involving moving free surfaces. The PFDPUS scheme is implemented into the CLAWPACK software for compressible problems, and in the Freeflow code for incompressible problems. The numerical results are compared with experimental, numerical and analytical data

In practical engineering applications involving extremely complex geometries, meshing typically constitutes a large portion of the overall design and analysis time. In the computational mechanics community, the ability to perform calculations on tetrahedral meshes has become increasingly important. For these reasons, automated tetrahedral mesh generation by means of Delaunay and advancing front techniques have recently received increasing attention in a number of applications, namely: crash impact simulations, cardiovascular modelling, blast and fracture modelling. Unfortunately, modern industry codes in solid mechanics typically rely on the use of traditional displacement based Finite Element formulations which possess several distinct disadvantages, namely: (1) reduced order of convergence for strains and stresses in comparison with displacements; (2) high frequency noise in the vicinity of shocks; and (3) numerical instabilities associated with shear locking, volumetric locking and pressure checker-boarding. In order to address the above mentioned shortcomings, a new mixed-based set of equations for solid dynamics formulated in a system of first order hyperbolic conservation laws was introduced. Crucially, the new set of conservation laws has a similar structure to that of the well known Euler equations in the context of Computational Fluid Dynamics (CFD). This enables us to borrow some of the available CFD technologies and to adapt the method in the context of solid dynamics. This thesis builds on the work carried out by Lee et al. 2013 by further developing the upwind cell centred finite volume framework for the numerical analysis of large strain explicit solid dynamics and its tailor-made implementation within the open source code OpenFOAM, extensively used in industrial and academic environments. The object oriented nature of OpenFOAM implementation provides a very efficient platform for future development. In this computational framework, the primary unknown variables are linear momentum and deformation gradient tensor of the system. Moreover, the formulation is further extended for an additional set of geometric strain measures comprising of the co-factor of deformation gradient tensor and the Jacobian of deformation, in order to simulate polyconvex constitutive models ensuring material stability. The domain is spatially discretised using a standard Godunov-type cell centred framework where second order accuracy is achieved by employing a linear reconstruction procedure in conjunction with a slope limiter. This leads to discontinuities in variables at the cell interface which motivate the use of a Riemann solver by introducing an upwind bias into the evaluation of numerical contact fluxes. The acoustic Riemann solver presented is further developed by applying preconditioned dissipation to improve its performance in the near incompressibility regime and extending its range to contact applications. Moreover, two evolutionary frameworks are proposed in this study to satisfy the underlying involutions (or compatibility conditions) of the system. Additionally, the spatial discretisation is alternatively represented through a nodal cell centred finite volume framework for comparison purposes. From a temporal discretisation point of view, a two stage Total Variation Diminishing Runge-Kutta time integrator is employed to ensure second order accuracy. Additionally, inclusion of a global posteriori angular momentum projection procedure enables preservation of angular momenta of the system. Finally, benchmark numerical examples are simulated to demonstrate various aspects of the formulation including mesh convergence, momentum preservation and the locking-free nature of the formulation on complex computational domains.<br>En aplicaciones prácticas de ingeniería que implican geometrías extremadamente complejas, el mallado requiere típicamente una gran parte del tiempo total de diseño y análisis. En la comunidad de mecánica computacional, la capacidad de realizar cálculos sobre mallas tetraédricas está siendo cada vez más importante. Por estas razones, la generación automatizada de mallas tetraédricas por medio de técnicas de Delaunay y frente avanzado han recibido cada vez más atención en ciertas aplicaciones, a saber: simulaciones de impacto, modelado cardiovascular, modelado de explosión y fractura. Por desgracia, los códigos en la industria moderna para mecánica de sólidos se basan normalmente en el uso de formulaciones tradicionales de Elementos Finitos formulados en desplazamientos que poseen varias desventajas: (1) menor orden de convergencia para tensiones y deformaciones; (2) ruido de alta frecuencia cerca de las ondas de choque; y (3) inestabilidades numéricas asociadas con el bloqueo a cortante, el bloqueo volumétrico y oscilaciones de presión. Con el fin de abordar estas deficiencias, se introduce un nuevo conjunto de ecuaciones para mecánica del sólido formulada como un sistema de leyes de conservación de primer orden basada en una formulación mixta. Fundamentalmente, el nuevo sistema de leyes de conservación tiene una estructura similar a la de las famosas ecuaciones de Euler en el contexto de la Dinámica de Fluidos Computacional (CFD). Esto nos permite aprovechar algunas de las tecnologías CFD disponibles y adaptar el método en el contexto de la Mecánica de Sólidos. Esta tesis se basa en el trabajo realizado en Lee et al. 2013 mediante el desarrollo de la estructura de volúmenes finitos centrados en celdas upwind para el análisis numérico de dinámica del sólido explícita en grandes deformaciones y su implementación específicamente diseñada dentro del software de código abierto OpenFOAM, ampliamente utilizado ámbito académico e industrial. Además, la naturaleza orientada a objetos de su implementación proporciona una plataforma muy eficiente para su desarrollo posterior. En este marco computacional, las incógnitas básicas de este sistema son el momento lineal y el tensor gradiente de deformación. Asimismo, la formulación se extiende adicionalmente para un conjunto adicional de medidas de deformación que comprenden el cofactor del tensor gradiente de deformación y el jacobiano de deformación, con el fin de simular modelos constitutivos policonvexos que aseguran la estabilidad del material. El dominio se discretiza espacialmente usando un marco centrado en células de tipo Godunov estándar, donde se consigue la precisión de segundo orden empleando un procedimiento de reconstrucción lineal junto con un limitador de pendiente. Esto conduce a discontinuidades en las variables en la interfase de la célula que motivan el uso de un solucionador de Riemann mediante la introducción de un sesgo contra el viento en la evaluación de flujos de contacto numéricos. El presente solucionador acústico de Riemann es posteriormente desarrollado aplicando disipación pre-condicionada para mejorar su rendimiento en el cercano pero incompresibilidad régimen y extender su gama a aplicaciones de contacto. Además, se proponen dos marcos evolutivos en este estudio para satisfacer las involuciones subyacentes (o condiciones de compatibilidad) del sistema. Además, la discretización espacial se representa alternativamente a través de un marco de volumen finito centrado en células nodales para fines de comparación. Desde el punto de vista de la discretización temporal, se emplea un integrador temporal de Runge-Kutta de dos etapas con Disminución de Variación Total para asegurar segundo orden de precision. Finalmente, se simulan ejemplos numéricos de referencia para demostrar varios aspectos de la formulación que incluyen convergencia de malla, conservación de momento y la naturaleza libre de bloqueo de la formulación en dominios computacionales complejos.

Lors que nous examinons numériquement des phénomènes multiphasiques suite à un accidentgrave dans le réacteur nucléaire, la dimension caractéristique des zones multi-fluides(non-réactifs et réactifs) s'avère beaucoup plus petite que celle du bâtiment réacteur, cequi fait la Simulation Numérique Directe de la configuration à peine réalisable. Autrement,nous proposons de considérer la zone de mélange multiphasique comme une interface infinimentfine. Puis, le solveur de Riemann réactif est inséré dans la Méthode des ÉquationsDiscrètes Réactives (RDEM) pour calculer le front de combustion à grande vitesse représentépar une interface discontinue. Une approche anti-diffusive est ensuite couplée avec laRDEM afin de précisément simuler des interfaces réactives. La robustesse et l'efficacité decette approche en calculant tant des interfaces multiphasiques que des écoulements réactifssont à la fois améliorées grâce à la méthode ici proposée : upwind downwind-controlled splitting(UDCS). UDCS est capable de résoudre précisément des interfaces avec les maillagesnon-structurés multidimensionnels, y compris des fronts réactifs de détonation et de déflagration.

Apesar de as EDPS que modelam leis de conservação e problemas em dinâmica dos fluídos serem bem estabelecidas, suas soluções numéricas continuam ainda desafiadoras. Em particular, há dois desafios associados à computação e ao entendimento desses problemas: um deles é a formação de descontinuidades (choques) e o outro é o fenômeno turbulência. Ambos os desafios podem ser atribuídos ao tratamento dos termos advectivos não lineares nessas equações de transporte. Dentro deste canário, esta tese apresenta o estudo do desenvolvimento de um novo esquema \"upwind\" de alta resolução e sua associação com modelagem da turbulência. O desempenho do esquema é investigado nas soluções da equação de advecção 1D com dados iniciais descontínuos e de problemas de Riemann 1D para as equações de Burgers, Euler e águas rasas. Além disso, são apresentados resultados numéricos de escoamentos incompressíveis 2D e 3D no regime laminar a altos números de Reynolds. O novo esquema é então associado à modelagem \'capa\' - \'epsilon\' da turbulência para a simulação numérica de escoamentos incompressíveis turbulentos 2D e 3D com superfícies livres móveis. Aplicação, verificação e validação dos métodos numéricos são também fornecidas<br>Althought the PDEs that model conservation laws and fluid dynamics problems are well established, their numerical solutions have presented a continuing challenge. In particular, there are two challenges associated with the computation and the understanding of these problems, namely, formation of shocks and turbulence. Both challenges can be attributed to the nonlinear advection terms of these transport equations. In this scenario, this thesis presents the study of the development of a new high-resolution upwind scheme and its association with turbulence modelling. The performance of the scheme is investigated by solving the 1D advection equation with discontinuous initial data 1D Riemann problems for Burgers, Euler and shallow water equations. Besides, numerical results for 2D and 3D incompressible laminar flows at high Reynolds number are presented. The new scheme is then associated with the \'capa - \' epsilon\' turbulence model for the simulation of 2D and 3D incompressible turbulent flows with moving free surfaces. Application, verification and validation of the numerical methods are also provided

Uma parte significativa dos escoamentos encontrados em aplicações tecnológicas é caracterizada por envolver altos números de Reynolds, principalmente aqueles em regime turbulento e com superfície livre. Obter soluções numéricas representativas para essa classe de problemas é extremamente difícil, devido à natureza não-linear das equações diferenciais parciais envolvidas nos modelos. Conseqüentemente, o tema tem sido uma das principais preocupações da comunidade científica moderna em dinâmica de fluidos computacional. Aproximações de primeira ordem para os termos convectivos são as mais adequadas para amortecer oscilações que estão associadas às aproximações de alta ordem não-limitadas. Todavia, elas introduzem dissipação artificial nas representações discretas comprometendo os resultados numéricos. Para minimizar esse efeito não-físico e, ao mesmo tempo, conseguir aproximações incondicionalmente estáveis, é indispensável adotar uma estratégia que combine aproximações de primeira ordem com as de ordem mais alta e que leve em conta a propagação de informações físicas. Os resultados dessa composição são os esquemas "upwind" limitados de alta ordem. Em geral, espera-se que esses esquemas sejam apropriados para a representação das derivadas convectivas nos modelos de turbulência kappa-varepsilon. No contexto de diferenças finitas, a presente tese dedica-se à solução numérica das equações de Navier-Stokes no regime de números de Reynolds elevados. Em particular, ela contém uma análise de algoritmos monotônicos e antidifusivos e modelos de turbulência kappa-varepsilon para a simulação de escoamentos incompressíveis envolvendo superfícies livres. Esquemas de convecção são implementados nos códigos GENSMAC para proporcionar um tratamento robusto dos termos convectivos nas equações de transporte. Duas versões do modelo kappa-varepsilon de turbulência são implementadas nos códigos GENSMAC, para problems bidimensionais e com simetria radial, para descrever os efeitos da turbulência sobre o escoamento médio. Resultados numéricos de escoamentos com simetria radial são comparados com resultados experimentais e analíticos. Simulações numéricas de problemas tridimensionais complexos são apresentadas para avaliar o desempenho de esquemas "upwind". Finalmente, os modelos de turbulência kappa-varepsilon são utilizados para a simulação de escoamentos confinados e com superfícies livres.<br>A considerable part of fluid flows encountered in technological applications is characterised by involving high-Reynolds numbers, especially those in turbulent regime and with free-surface. It is extremely difficult to obtain representative numerical solutions for this class of problems, due to the non-linear nature of the partial differential equations involved in the models. Consequently, this subject has been one of main concerns in the modern computational fluid dynamics community. First-order approximation to the convective terms is one of the most appropriate to smooth out oscilations/instabilities which are associated with high-order unlimited approximation. However, it introduces numerical dissipation in the discrete representation jeopardizing the numerical results. In order to minimize this non-physical effect and, at the same time, to obtain unconditionally stable approximation, it is essential to adopt a strategy that combines first and high-order approximations and takes into account the propagation of physical information. The results of this composition are the high-order bounded upwind techniques. In general, it is expected that these algorithms are satisfactory for the representation of the convective derivatives in the kappa-varepsilon turbulence model. In the context of finite-difference, the present thesis deals with the numerical solution of the Navier-Stokes equations at high-Reynolds number regimes. In particular, it contains an analysis of monotonic and anti-difusive convection schemes and kappa-varepsilon turbulence models for the simulation of free-surface fluid flows. Upwinding methods are implemented into the GENSMAC codes to provide a robust treatment of the convective terms in the transport equations. Two versions of the K-Epsilon turbulence model are implemented into the two-dimensional and axisymmetric GENSMAC codes, in order to describe the turbulent effects on the average flow. Numerical results of axisymmetric flows are compared with experimental and analytical results. Numerical simulations of complex three-dimensional problems are presented to assess the performance of high-order bounded upwind schemes. Finally, the K-Epsilon turbulence models are employed in the simulation of confined and free-surface flows.