Academic literature on the topic 'Solveur de Riemann RSM-RANS'
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Journal articles on the topic "Solveur de Riemann RSM-RANS"
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Chuvakhov, P. V. "A Riemann solver for RANS." Computational Mathematics and Mathematical Physics 54, no. 1 (January 2014): 135–47. http://dx.doi.org/10.1134/s0965542514010072.
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Chuvakhov, Pavel Vladimirovich. "ON A RIEMANN SOLVER FOR THREE-DIMENSIONAL RANS." Computational Thermal Sciences: An International Journal 6, no. 5 (2014): 369–81. http://dx.doi.org/10.1615/computthermalscien.2014010968.
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Hien, Le Thi Thu, and Nguyen Van Chien. "Investigate Impact Force of Dam-Break Flow against Structures by Both 2D and 3D Numerical Simulations." Water 13, no. 3 (January 30, 2021): 344. http://dx.doi.org/10.3390/w13030344.
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The aim of this paper was to investigate the ability of some 2D and 3D numerical models to simulate flood waves in the presence of an isolated building or building array in an inundated area. Firstly, the proposed 2D numerical model was based on the finite-volume method (FVM) to solve 2D shallow-water equations (2D-SWEs) on structured mesh. The flux-difference splitting method (FDS) was utilized to obtain an exact mass balance while the Roe scheme was invoked to approximate Riemann problems. Secondly, the 3D commercially available CFD software package was selected, which contained a Flow 3D model with two turbulent models: Reynolds-averaged Navier-Stokes (RANs) with a renormalized group (RNG) and a large-eddy simulation (LES). The numerical results of an impact force on an obstruction due to a dam-break flow showed that a 3D solution was much better than a 2D one. By comparing the 3D numerical force results of an impact force acting on building arrays with the existence experimental data, the influence of velocity-induced force on a dynamic force was quantified by a function of the Froude number and the water depth of the incident wave. Furthermore, we investigated the effect of the initial water stage and dam-break width on the 3D-computed results of the peak value of force intensity.
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Leloudas, Stavros N., Georgios N. Lygidakis, Argiris I. Delis, and Ioannis K. Nikolos. "An artificial compressibility method for axisymmetric swirling flows." Engineering Computations ahead-of-print, ahead-of-print (June 17, 2021). http://dx.doi.org/10.1108/ec-10-2020-0594.
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Purpose This study aims to feature the application of the artificial compressibility method (ACM) for the numerical prediction of two-dimensional (2D) axisymmetric swirling flows. Design/methodology/approach The respective academic numerical solver, named IGal2D, is based on the axisymmetric Reynolds-averaged Navier–Stokes (RANS) equations, arranged in a pseudo-Cartesian form, enhanced by the addition of the circumferential momentum equation. Discretization of spatial derivative terms within the governing equations is performed via unstructured 2D grid layouts, with a node-centered finite-volume scheme. For the evaluation of inviscid fluxes, the upwind Roe’s approximate Riemann solver is applied, coupled with a higher-order accurate spatial reconstruction, whereas an element-based approach is used for the calculation of gradients required for the viscous ones. Time integration is succeeded through a second-order accurate four-stage Runge-Kutta method, adopting additionally a local time-stepping technique. Further acceleration, in terms of computational time, is achieved by using an agglomeration multigrid scheme, incorporating the full approximation scheme in a V-cycle process, within an efficient edge-based data structure. Findings A detailed validation of the proposed numerical methodology is performed by encountering both inviscid and viscous (laminar and turbulent) swirling flows with axial symmetry. IGal2D is compared against the commercial software ANSYS fluent – by using appropriate metrics and characteristic flow quantities – but also against experimental measurements, confirming the proposed methodology’s potential to predict such flows in terms of accuracy. Originality/value This study provides a robust methodology for the accurate prediction of swirling flows by combining the axisymmetric RANS equations with ACM. In addition, a detailed description of the convective flux Jacobian is provided, filling a respective gap in research literature.
Dissertations / Theses on the topic "Solveur de Riemann RSM-RANS"
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Ben, Nasr Nabil. "Aérodynamique 3-D : application au bruit des soufflantes des turboréacteurs." Paris 6, 2010. http://www.theses.fr/2010PA066117.
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La réduction du bruit des avions aux environs des zones aéroporturaires est devenu un enjeu socio-économique majeur. En effet, du fait de l'augmentation continue du nombre de vol, mais aussi de la capacité, et donc de la taille des avions, le traffic aérien est en constante croissance. De par les forts niveaux sonores émis par les aéronefs, cette croissance compromet l'intégration harmonieuse de l'activité aéronautique commerciale au sein de l'environnement. C'est pourquoi avionneurs et motoristes se soucient de plus en plus de la réduction des émissions acoustiques. Si la réduction du bruit des avions est une notion claire, elle s'avère être un problème des plus difficiles. Les divers émissions sonores au décollage ou en approche font intervenir des mécanismes physiques nombreux et encore mal connus. Le conseil consultatif pour la recherche aéronautique en Europe a fixé deux objectifs : répondre aux besoins de la société en terme de transport aérien plus efficace, plus sûre et respectueux de l'environnement et assurer la compétitivité de l'industrie aéronautique européenne. Afin de pouvoir répondre à cet objectif, la Communauté européenne a mis sur pieds des projets, dont : PROBAND et VITAL pour pouvoir comprendre d'une part les phénomènes et les sources acoustiques du bruit à large bande et d'étudier des configurations innovantes. Cette thèse a donc pour but de réaliser des calculs stationnaires (RMS-RANS) et instationnaires (RMS-RANS en utilisant l'approche chorochronique) pour des configurations de turboréacteurs à double flux et fournir les données nécessaires afin de pouvoir prédire le niveau acoustique émit.
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Sénéchal, Dorothée. "DNS des écoulements turbulents compressibles : fluctuations de pression, de masse volumique et de température." Paris 6, 2009. http://www.theses.fr/2009PA066106.
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Cette thèse traite du développement de méthodes numériques d'ordre élevé possédant de bonnes propriétés de capture de choc pour la résolution directe des équations Navier-Stokes compressibles. Le solveur DNS implémenté utilise des reconstructions d'ordre élevé UW et WENO/M (UW17/WENOM17) et un solveur de Riemann approché faiblement diffusif HLLC. L'intégration temporelle est implicite, précise à l'ordre deux et utilise une procédure de pas de temps dual avec sous-itérations explicites. Les calculs DNS compressibles dans un canal plan 3-D ont permis d'évaluer la dissipation numérique des schémas UW et WENO/M et l'effet de la résolution du maillage sur la prédiction des statistiques turbulentes. De nouveaux schémas d'ordre élevé (WENOM17) ont été développés. Une analyse de l'effet de la taille de boîte du canal plan sur la prédiction du champ turbulent a été réalisée. La base de données DNS compressible a permis d'effectuer une analyse détaillée de l'évolution des quantités thermodynamiques fluctuantes (', p' et T'') qui sont fortement corrélées en présence de parois isothermes. Une modélisation tensorielle de l'équation de transport pour '_rms a été proposée et validée en a priori et a posteriori. Une décomposition des fluctuations de pression en cinq termes a été appliquée aux corrélations qui interviennent dans l'équation de transport des tensions de Reynolds des modèles RSM. Cette décomposition permettra d'évaluer séparement les parties homogène et inhomogène de la diffusion de pression et du tenseur de redistribution du transport des tensions de Reynolds.
Conference papers on the topic "Solveur de Riemann RSM-RANS"
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Lee, Hyungro, Einkeun Kwak, and Seungsoo Lee. "Artificial Compressibility Method and Preconditioning Method for Solving Two Dimensional Incompressibile Flow." In ASME-JSME-KSME 2011 Joint Fluids Engineering Conference. ASMEDC, 2011. http://dx.doi.org/10.1115/ajk2011-01007.
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In this study, two commonly used numerical methods for the analysis of incompressible flows (or low Mach number flows), Chorins’ artificial compressibility method and Wiess and Smith’s preconditioning method are compared. Also, the convergence characteristics of two methods are numerically investigated for two-dimensional laminar and turbulent flows. Although the two methods have similar governing equations, the eigensystems and other details are very different. The eigensystems of the artificial compressibility method and the preconditioning method are analytically examined. An artificial compressibility code that solves the incompressible RANS (Reynolds Averaged Navier-Stokes) equations is newly developed for the study. An artificial compressibility code and a well-verified existing low Mach number code uses Roe’s approximate Riemann solver in conjunction with a cell centered finite volume method. Using MUSCL extrapolation with nonlinear limiters, 2nd order spatial accuracy is achieved while maintaining TVD (total variation diminishing) property. AF-ADI (approximate factorization-alternate direction implicit) method is used to get the steady solution for both codes. Menter’s k–ω SST turbulence model is used for the analysis of turbulent flows. Navier-Stokes equations and the turbulence model equations are solved in a loosely coupled manner.
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Rafiee, Ashkan, Bjoern Elsaesser, and Frederic Dias. "Numerical Simulation of Wave Interaction With an Oscillating Wave Surge Converter." In ASME 2013 32nd International Conference on Ocean, Offshore and Arctic Engineering. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/omae2013-10195.
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This paper deals with numerical studies of wave interaction with an Oscillating Wave Surge Converters (OWSC) using a Godunov–type SPH method. The use of a Riemann solver in calculating the density field results in a smoother SPH pressure field. Hence, a more accurate estimation of loads on the OWSC is achieved. Furthermore, the Lagrangian form of the RANS k–ε model is included in the SPH equations to better capture the turbulent features of the flow. SPH simulations were performed in both two–dimensions (2D) and three–dimensions (3D) and results for the flow pattern and loads are compared with experimental data.
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Kwak, Einkeun, Sang-il Park, Namhun Lee, and Seungsoo Lee. "Aerodynamic Performance Evaluation of 3D Aircraft Configurations by Turbulence Models." In ASME-JSME-KSME 2011 Joint Fluids Engineering Conference. ASMEDC, 2011. http://dx.doi.org/10.1115/ajk2011-15014.
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Numerical simulations of 3D aircraft configurations are performed in order to understand the effects that turbulence models have on the aerodynamic characteristics of an aircraft. An in-house CFD code that solves 3D RANS equations and 2-equation turbulence model equations is used for the study. The code applies Roe’s approximated Riemann solver and an AF-ADI scheme. Furthermore van Leer’s MUSCL extrapolation with van Albada’s limiter is adopted. Various versions of Menter’s k-omega SST turbulence models as well as Coakley’s q-omega model are incorporated into the CFD code. Menter’s k-omega SST models include the standard model, the 2003 model, the model incorporating the vorticity source term, and the model containing controlled decay. Turbulent flows over a wing are simulated in order to validate the turbulence models contained in the CFD code. The results from these simulations are then compared to computational results of the 3rd AIAA CFD Drag Prediction Workshop. Moreover, numerical simulations of the DLR-F6 wing-body and wing-body-nacelle-pylon configurations are conducted and compared to computational results of the 2nd AIAA CFD Drag Prediction Workshop. Especially, the aerodynamic characteristics as well as flow features with respect to the turbulence models are scrutinized. The results obtained from each simulation incorporating Menter’s k-omega SST turbulence model variations are compared with one another.
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Ma, Can, Xinrong Su, Jinlan Gou, and Xin Yuan. "Runge-Kutta/Implicit Scheme for the Solution of Time Spectral Method." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-26474.
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This paper investigates the Runge-Kutta implicit scheme applied to the solution of the time spectral method for periodic unsteady flow simulation. Several explicit and implicit time integration schemes including the Runge-Kutta scheme, Block-Jacobi SSOR (symmetric successive over relaxation)scheme and Block-Jacobi Runge-Kutta/Implicit scheme are implemented into an in-house code and applied to the time marching solution of the time spectral method. The time integration is coupled with Full Approximation Storage (FAS) type multi-grid method for convergence acceleration. The in-house code is based on the finite volume method and solves the RANS (Reynolds Averaged Navier-Stokes) equations on multi-block structured mesh. For spatial discretization the 3rd/5th order WENO (weighted essentially nonoscillatory) upwind scheme is used for reconstruction and the convective flux is computed with Roe approximate Riemann solver. The widely used one-equation Spalart-Allmaras turbulence model is used in the simulations. The time integration schemes for the solution of the time spectral method are tested with two different compressor cascades with periodically oscillating inlet boundary conditions. The first case is a low speed compressor stator with inlet flow angle varying with time. The second case is a high speed compressor rotor with inlet boundary condition profile to simulation the influence of upstream wakes. The results show that for moderate frequencies and wave mode numbers, the Block-Jacobi Runge-Kutta/Implicit scheme shows favorable convergence behavior compared to the other schemes. However, for extremely high frequencies and wave mode numbers such as in the simulation of high rotating speed compressors, the advantage of the Block-Jacobi Runge-Kutta/Implicit scheme over the explicit Runge-Kutta scheme is totally lost.