Dans le cycle de vie logiciel nous avons principalement les activités (1) de pré-développement (l'analyse des besoins, les spécifications, la conception architecturale et la conception détaillée), (2) de développement (l'implémentation, le prototypage, les tests unitaires et les tests d'intégration) et (3) de post-développement (déploiement). Le déploiement de logiciel couvre l'ensemble des activités post-développement. Les activités de déploiement permettent de rendre une application utilisable. Elles sont identifiées comme cycle de vie de déploiement couvrant l'archivage des logiciels, leur chargement, leur installation sur les sites clients, leur configuration, leur activation ainsi que leur mise à jour. Le développement de systèmes à composants a permis de mieux identifier cette partie du cycle de vie global du logiciel, comme le montrent de nombreux travaux industriels et académiques. Cependant ces travaux sont en général développés de manière ad' hoc, spécifiques à une plate-forme donnée. Peu flexibles, ils s'adaptent difficilement aux stratégies des entreprises. Les systèmes de déploiement comme le montrent ceux supportés par les environnements de type intergiciel CCM, .Net, EJB développent de manière spécifique les mécanismes et outils de déploiement et introduisent des choix prédéfinis et figés de stratégies de déploiement. Nos travaux se situent dans le contexte de logiciels à base de composants distribués et portent sur la proposition d'un environnement générique pour supporter leur déploiement. C'est une nouvelle génération de systèmes proposée essentiellement par le monde académique de génie logiciel qui s'est approprié la problématique de déploiement à large échelle. Dans ce contexte, nous proposons une approche basée sur l'ingénierie dirigée par les modèles où nous introduisons les abstractions nécessaires pour décrire les logiciels à déployer, les infrastructures de déploiement, les stratégies de déploiement ainsi que le processus de déploiement avec l'identification et l'ordonnancement des activités à accomplir et le support pour leur exécution.

Este trabalho apresenta o resultado da aplicação do Método dos Volumes Finitos, adotado pelo software comercial Star-CCM+ na simulação para o regime permanente de escoamentos turbulentos incompressíveis e compressíveis sobre seções de aerofólios. Para o caso incompressível modelam-se seções do aerofólio NACA 0012 com ângulo de ataque zero. Para o caso compressível, uma seção do aerofólio supercrítico OAT15A em pequeno ângulo de ataque é modelada. Os domínios computacionais são discretizados por malhas não estruturadas de células poliédricas ou por malhas estruturadas de geração hiperbólica para diferentes topologias e parâmetros construtivos determinados pela estimativa de grandezas do fenômeno físico, como a altura da primeira camada de células quadrilaterais junto à parede. A qualidade e adequação dessas malhas para as simulações são verificadas por estudo de dependência quanto ao nível de refinamento e também quanto à posição do contorno onde o escoamento é livre no caso de escoamento compressível. Na metodologia de verificação, o índice de convergência de malha GCI e a ordem observada de convergência do método (dos Volumes Finitos) são obtidos para três níveis de refinamento com o propósito de selecionar uma malha de trabalho que concilie precisão e esforço computacional com os recursos disponíveis. As simulações são conduzidas para dois modelos de turbulência – o modelo Spalart-Allmaras e o modelo k-ω/SST. Os resultados obtidos pela aplicação desses modelos são interpretados sob o ponto de vista fenomenológico e comparados com os resultados experimentais disponíveis em literatura. / The Finite Volumes Method adopted by the commercial software Star-CCM+ is applied to the simulation of the steady state regime of incompressible and compressible turbulent flows over selected airfoil’s sections. The physical model used with the incompressible flow case is a NACA 0012 airfoil section at zero angle of attack. The ONERA’s OAT15A supercritical airfoil section at small angle of attack applies to the compressible flow case. The computational domains are discretized by structured and unstructured meshes for different topologies and far field configurations. The structured meshes are of the quadrilateral type with hyperbolic node distribution whilst the unstructured meshes use polyhedral cells. The grids are generated by applying a methodology where estimates of the flow variables are used as input for the grid’s constructive parameters like the near wall cell thickness. Grid dependency studies are carried out in order to verify the grid’s quality and suitability to represent the physical phenomena. The grid’s asymptotic convergence index GCI and its observed order of convergence are evaluated for three refinement levels and far field position for the compressible flow cases. The objective is to select the most suitable grid taking into account the accuracy requirements and the computational resources available. The one-equation Spalart-Allmaras turbulence model and the two-equation k-ω/SST turbulence models are used. The numerical results are discussed from the physical point of view and compared with the experimental ones available in literature.

Este trabalho apresenta o resultado da aplicação do Método dos Volumes Finitos, adotado pelo software comercial Star-CCM+ na simulação para o regime permanente de escoamentos turbulentos incompressíveis e compressíveis sobre seções de aerofólios. Para o caso incompressível modelam-se seções do aerofólio NACA 0012 com ângulo de ataque zero. Para o caso compressível, uma seção do aerofólio supercrítico OAT15A em pequeno ângulo de ataque é modelada. Os domínios computacionais são discretizados por malhas não estruturadas de células poliédricas ou por malhas estruturadas de geração hiperbólica para diferentes topologias e parâmetros construtivos determinados pela estimativa de grandezas do fenômeno físico, como a altura da primeira camada de células quadrilaterais junto à parede. A qualidade e adequação dessas malhas para as simulações são verificadas por estudo de dependência quanto ao nível de refinamento e também quanto à posição do contorno onde o escoamento é livre no caso de escoamento compressível. Na metodologia de verificação, o índice de convergência de malha GCI e a ordem observada de convergência do método (dos Volumes Finitos) são obtidos para três níveis de refinamento com o propósito de selecionar uma malha de trabalho que concilie precisão e esforço computacional com os recursos disponíveis. As simulações são conduzidas para dois modelos de turbulência – o modelo Spalart-Allmaras e o modelo k-ω/SST. Os resultados obtidos pela aplicação desses modelos são interpretados sob o ponto de vista fenomenológico e comparados com os resultados experimentais disponíveis em literatura. / The Finite Volumes Method adopted by the commercial software Star-CCM+ is applied to the simulation of the steady state regime of incompressible and compressible turbulent flows over selected airfoil’s sections. The physical model used with the incompressible flow case is a NACA 0012 airfoil section at zero angle of attack. The ONERA’s OAT15A supercritical airfoil section at small angle of attack applies to the compressible flow case. The computational domains are discretized by structured and unstructured meshes for different topologies and far field configurations. The structured meshes are of the quadrilateral type with hyperbolic node distribution whilst the unstructured meshes use polyhedral cells. The grids are generated by applying a methodology where estimates of the flow variables are used as input for the grid’s constructive parameters like the near wall cell thickness. Grid dependency studies are carried out in order to verify the grid’s quality and suitability to represent the physical phenomena. The grid’s asymptotic convergence index GCI and its observed order of convergence are evaluated for three refinement levels and far field position for the compressible flow cases. The objective is to select the most suitable grid taking into account the accuracy requirements and the computational resources available. The one-equation Spalart-Allmaras turbulence model and the two-equation k-ω/SST turbulence models are used. The numerical results are discussed from the physical point of view and compared with the experimental ones available in literature.

Este trabalho apresenta o resultado da aplicação do Método dos Volumes Finitos, adotado pelo software comercial Star-CCM+ na simulação para o regime permanente de escoamentos turbulentos incompressíveis e compressíveis sobre seções de aerofólios. Para o caso incompressível modelam-se seções do aerofólio NACA 0012 com ângulo de ataque zero. Para o caso compressível, uma seção do aerofólio supercrítico OAT15A em pequeno ângulo de ataque é modelada. Os domínios computacionais são discretizados por malhas não estruturadas de células poliédricas ou por malhas estruturadas de geração hiperbólica para diferentes topologias e parâmetros construtivos determinados pela estimativa de grandezas do fenômeno físico, como a altura da primeira camada de células quadrilaterais junto à parede. A qualidade e adequação dessas malhas para as simulações são verificadas por estudo de dependência quanto ao nível de refinamento e também quanto à posição do contorno onde o escoamento é livre no caso de escoamento compressível. Na metodologia de verificação, o índice de convergência de malha GCI e a ordem observada de convergência do método (dos Volumes Finitos) são obtidos para três níveis de refinamento com o propósito de selecionar uma malha de trabalho que concilie precisão e esforço computacional com os recursos disponíveis. As simulações são conduzidas para dois modelos de turbulência – o modelo Spalart-Allmaras e o modelo k-ω/SST. Os resultados obtidos pela aplicação desses modelos são interpretados sob o ponto de vista fenomenológico e comparados com os resultados experimentais disponíveis em literatura. / The Finite Volumes Method adopted by the commercial software Star-CCM+ is applied to the simulation of the steady state regime of incompressible and compressible turbulent flows over selected airfoil’s sections. The physical model used with the incompressible flow case is a NACA 0012 airfoil section at zero angle of attack. The ONERA’s OAT15A supercritical airfoil section at small angle of attack applies to the compressible flow case. The computational domains are discretized by structured and unstructured meshes for different topologies and far field configurations. The structured meshes are of the quadrilateral type with hyperbolic node distribution whilst the unstructured meshes use polyhedral cells. The grids are generated by applying a methodology where estimates of the flow variables are used as input for the grid’s constructive parameters like the near wall cell thickness. Grid dependency studies are carried out in order to verify the grid’s quality and suitability to represent the physical phenomena. The grid’s asymptotic convergence index GCI and its observed order of convergence are evaluated for three refinement levels and far field position for the compressible flow cases. The objective is to select the most suitable grid taking into account the accuracy requirements and the computational resources available. The one-equation Spalart-Allmaras turbulence model and the two-equation k-ω/SST turbulence models are used. The numerical results are discussed from the physical point of view and compared with the experimental ones available in literature.

This thesis deals with CFD simulation of platooning vehicles and their aerodynamic characteristics, created in Star CCM+ software. The main focus is on their aerodynamic drag dependency on different spacing between vehicles which allowed to evaluate the most energy efficient distance for platoon of vehicles. Furthermore, the procedure how to calculate the fuel consumption is described for set of variables.

This diploma thesis is focused on the implementation of the technology VoIP in the remote branch offices of a big company. There are used the current WAN lines, which have been so far used only for transfer of data. Implementation of IP telephony is extending the utilization of those lines and at the same time the costs for running of the telephone services are reduced. There are described the models for proposal and also the proposal for solution of IP telephony for a specific company.

No description available.

Configurable computing machines (CCMs) offer high-performance application acceleration with custom hardware. They are also dynamically reconfigurable and give significant internal visibility. Such features are useful throughout the design, debug, and deploy stages of CCM-based application development. However traditional, monolithic design tools do not offer adequate support for all of these development stages. This thesis describes a specification for a reconfigurable computing application framework (RCAF) which is more suitable for CCM application development. It also describes an implementation of such an RCAF. This RCAF improves the efficiency of application design and debugging. It also establishes an application architecture framework which helps to build up not only the hardware design, but also the application software and user interface. Applications built using this small, deployable RCAF may also perform significantly better due to the dynamic hardware reconfiguration features included with the RCAF.

This project deals with the CFD modelling of a free surface flow. The aim is to develop and validate a fast and accurate numerical model for stratified two-phase flows. Volume of Fluid (VOF) multiphase model is employed. The purpose is to use the developed numerical model for the design of an element within a compact nuclear reactor.Unsteady Reynolds Averaged Navier-Stokes (RANS) simulations are conducted. Two free surface test cases are simulated to verify and ensure robustness of the model: a dam break and a vertical cylindrical obstacle set in a channel. From there, an optimization is performed in order to find the best compromise between accuracy and rapidity with the solver. The proper set of parameter models is found by carrying out extensive sensitivity studies and compare the solutions with available measurements.The obtained numerical results show a reasonable good agreement with the experimental data for the dam-break. Significant time savings are achieved thanks to the implemented optimization process while maintaining accuracy. The optimized model is then applied to the second test case and comparisons with experimental measurements are carried out. The same physical behavior of the flow as in experiments is captured with the simulations. The differences found between the simulation data and experiments are partly due to the difficulty to monitor experimentally with a high accuracy the highly non uniform regions within the flow.

<p>Supercritical Water-cooled Reactor (SCWR) is a Generation-IV nuclear reactor design that operates on a direct energy conversion cycle above the thermodynamic critical point of water (374⁰C and 22.1 MPa), and offers higher thermal efficiency and considerable design simplification. As an essential step in the design of SCWR safety systems, the accident behaviour of the reactor is evaluated to ensure that the safety systems can achieve safe shutdown for all the design basis accidents. Unfortunately, the computational tools and computer codes that are currently employed for safety analysis have little application in the supercritical region, and faces significant challenges in simulating the transitions from subcritical to supercritical conditions.</p> <p>This thesis examines the predictive capabilities of Computational Fluid Dynamics (CFD) code STAR-CCM+ by evaluating critical flow (or choked flow) due to accidental release of coolant from supercritical fluid systems. The biggest challenge of this research is that the current version of STAR-CCM+ does not support supercritical simulations because the steam tables included in the package are only limited to the subcritical subset of the thermodynamic fluid properties.</p> <p>The research was carried out in two stages. In the first stage, the CFD code STAR-CCM+ was customized to simulate supercritical conditions by, (i) Generating updated steam tables to include subcritical and supercritical fluid properties and using more pressure and temperature points in the pseudo critical region (22 – 25 MPa, 645 -660 K) to handle the rapid changes in the fluid properties, and (ii) Implementing a multi-dimensional steam table interpolation scheme to access the fluid property data at any thermodynamic state during the simulation. In the second stage, the customized CFD code was extensively evaluated by simulating several accidental release scenarios from supercritical conditions using rounded-edge and sharp-edge nozzles and the model results were validated with experimental data. To overcome the solution stability (or convergence) issues encountered during the supercritical simulations, a fine tuning procedure was proposed that guaranteed convergence for all the case studies considered in this thesis.</p> <p>The simulation results revealed that the CFD model produced results that were in good agreement with experimental data and only about 10% prediction error was noticed for most cases considered in the thesis. Considering the sensitivity of the CFD model for upstream temperatures and pressures, these results appear to be quite reasonable. From the computational experience gained in this research , we believe that the CFD code STAR-CCM+ is a very useful tool to perform thermal hydraulic simulations for supercritical systems. However, an appropriate customization and extensive validation of the code is required before it can be exclusively used for safety analysis.</p> / Master of Applied Science (MASc)