Bibliografie tematiche / Équations de Reynolds-Averaged Navier Stokes

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Letteratura scientifica selezionata sul tema "Équations de Reynolds-Averaged Navier Stokes"

Autore: Grafiati
Pubblicato: 1 marzo 2025

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Articoli di riviste sul tema "Équations de Reynolds-Averaged Navier Stokes"

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Reliquet, Gabriel, Marie Robert, Lionel Gentaz, and Pierre Ferrant. "Simulations de l'interaction entre le catamaran Delft 372 et la houle à l'aide du couplage SWENSE-Level Set." La Houille Blanche, no. 5-6 (December 2019): 59–66. http://dx.doi.org/10.1051/lhb/2019030.

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Ce papier présente les derniers développements concernant le couplage de la méthode SWENSE (Spectral Waves Navier-Stokes Equations) et d'une méthode de résolution des équations RANS (Reynolds Averaged Navier-Stokes) avec capture d'interface de type Level Set. Ce couplage permet de combiner les avantages des deux méthodes, c'est-à-dire avoir une cinématique de houle de bonne qualité dans tout le domaine grâce à la méthode SWENSE et la prise en compte du déferlement via la fonction Level Set. Le catamaran Delft 372 est utilisé pour les validations avec des calculs sur mer calme et sur houle régulière à deux vitesses différentes.
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Seok, Woochan, Sang Bong Lee, and Shin Hyung Rhee. "Computational simulation of turbulent flows around a marine propeller by solving the partially averaged Navier–Stokes equation." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 233, no. 18 (2019): 6357–66. http://dx.doi.org/10.1177/0954406219848021.

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This study concerns the characteristics of the partially averaged Navier–Stokes method for local flow analysis around a rotating propeller. Partially averaged Navier–Stokes, resolving crucial large-scale structures of turbulent flow at a given computational grid resolution, is a bridging turbulence closure model between the Reynolds-averaged Navier–Stokes equation and the direct numerical simulation. A detailed comparison between partially averaged Navier–Stokes and Reynolds-averaged Navier–Stokes models is made to achieve a better understanding of partially averaged Navier–Stokes characteristics for predicting the coherent structures in turbulent flow. The two-equation k-ω shear stress transport model and the seven-equation Reynolds stress model are selected for Reynolds-averaged Navier–Stokes computations. The problem of interest is the flow around a rotating KP505 propeller in open water conditions at an advance ratio of 0.7. Near the leading edge, the partially averaged Navier–Stokes results are similar to those of Reynolds stress model in terms of the vortical structures. Vorticity predicted by different turbulence models, however, shows significant differences. For a more detailed analysis, the velocity gradient constituting the vorticity is identified at the leading edge. It is proven that partially averaged Navier–Stokes is able to capture the anisotropic characteristics of the flow at the leading edge, where both the geometric and flow characteristics change abruptly.
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Güemes, Alejandro, Pablo Fajardo, and Marco Raiola. "Experimental Assessment of RANS Models for Wind Load Estimation over Solar-Panel Arrays." Applied Sciences 11, no. 6 (2021): 2496. http://dx.doi.org/10.3390/app11062496.

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This paper reports a comparison between wind-tunnel measurements and numerical simulations to assess the capabilities of Reynolds-Averaged Navier-Stokes models to estimate the wind load over solar-panel arrays. The free airstream impinging on solar-panel arrays creates a complex separated flow at large Reynolds number, which is severely challenging for the current Reynolds-Averaged Navier-Stokes models. The Reynolds-Averaged Navier-Stokes models compared in this article are k-ϵ, Shear-Stress Transport k-ω, transition and Reynolds Shear Model. Particle Image Velocimetry measurements are performed to investigate the mean flow-velocity and turbulent-kinetic-energy fields. Pressure taps are located in the surface of the solar panel model in order to obtain static pressure measurements. All the Reynolds-Averaged Navier-Stokes models predict accurate average velocity fields when compared with the experimental ones. One of the challenging factor is to predict correctly the thickness of the turbulent wake. In this aspect, Reynolds Shear provides the best results, reproducing the wake shrink observed on the 3rd panel in the experiment. On the other hand, some other features, most notably the blockage encountered by the flow below the panels, are not correctly reproduced by any of the models. The pressure distributions over the 1st panel obtained from the different Reynolds-Averaged Navier-Stokes models show good agreement with the pressure measurements. However, for the rest of the panels Reynolds-Averaged Navier-Stokes fidelity is severely challenged. Overall, the Reynolds Shear model provides the best pressure estimation in terms of pressure difference between the front and back sides of the panels.
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Li, Tian, Li-Hao Zhao, Xiao-Ke Ku, Helge Andersson, and Terese Lovas. "Numerical investigation of particles turbulent dispersion in channel flow." Thermal Science 16, no. 5 (2012): 1510–14. http://dx.doi.org/10.2298/tsci1205510l.

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This paper investigates the performance of Reynolds-averaged Navier-Stokes model on dispersion of particles in wall turbulence. A direct numerical simulation of wall-bounded channel flow with particles suspensions was set as a benchmark. The standard k-? model coupled with two different eddy interaction models was used in Reynolds-averaged Navier-Stokes model and compared to the direct numerical simulation. Detailed comparisons between direct numerical simulation and Reynolds-averaged Navier-Stokes model on particle distribution evolving over time were carried out.
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Chakraborty, Arnab, and HV Warrior. "Study of turbulent flow past a square cylinder using partially-averaged Navier–Stokes method in OpenFOAM." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 234, no. 14 (2020): 2821–32. http://dx.doi.org/10.1177/0954406220910176.

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The present paper reports numerical simulation of turbulent flow over a square cylinder using a novel scale resolving computational fluid dynamics technique named Partially-Averaged Navier–Stokes (PANS), which bridges Reynolds-Averaged Navier–Stokes (RANS) with Direct Numerical Simulation (DNS) in a seamless manner. All stream-wise and wall normal mean velocity components, turbulent stresses behavior have been computed along the flow (streamwise) as well as in transverse (wall normal) direction. The measurement locations are chosen based on the previous studies so that results could be compared. However, the Reynolds number ( Re) of the flow is maintained at 21,400 and K– ω turbulence model is considered for the present case. All the computations are performed in OpenFOAM framework using a finite volume solver. Additionally, turbulent kinetic energy variations are presented over a wide range of measurement planes in order to explain the energy transfer process in highly unsteady turbulent flow field. The fluctuating root mean square velocities in the streamwise as well as in the wall normal direction have been discussed in the present work. It has been found that Partially-Averaged Navier–Stokes (PANS) model is capable of capturing the properties of highly unsteady turbulent flows and gives better results than Reynolds-Averaged Navier–Stokes (RANS). The results obtained using Partially-Averaged Navier–Stokes (PANS) are quite comparable with Large Eddy Simulation (LES) and Direct Numerical Simulation (DNS) data available in literature. The partially-averaged Navier–Stokes results are compared with our simulated Reynolds-Averaged Navier–Stokes (RANS) results, available experimental as well as numerical results in literature and it is found to be good in agreement.
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Sun, Bohua. "Revisiting the Reynolds-averaged Navier–Stokes equations." Open Physics 19, no. 1 (2021): 853–62. http://dx.doi.org/10.1515/phys-2021-0102.

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Abstract This study revisits the Reynolds-averaged Navier–Stokes (RANS) equations and finds that the existing literature is erroneous regarding the primary unknowns and the number of independent unknowns in the RANS. The literature claims that the Reynolds stress tensor has six independent unknowns, but in fact the six unknowns can be reduced to three that are functions of the three velocity fluctuation components, because the Reynolds stress tensor is simply an integration of a second-order dyadic tensor of flow velocity fluctuations rather than a general symmetric tensor. This difficult situation is resolved by returning to the time of Reynolds in 1895 and revisiting Reynolds’ averaging formulation of turbulence. The study of turbulence modeling could focus on the velocity fluctuations instead of the Reynolds stress. An advantage of modeling the velocity fluctuations is, from both physical and experimental perspectives, that the velocity fluctuation components are observable whereas the Reynolds stress tensor is not.
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Torner, Benjamin, Lucas Konnigk, Sebastian Hallier, Jitendra Kumar, Matthias Witte, and Frank-Hendrik Wurm. "Large eddy simulation in a rotary blood pump: Viscous shear stress computation and comparison with unsteady Reynolds-averaged Navier–Stokes simulation." International Journal of Artificial Organs 41, no. 11 (2018): 752–63. http://dx.doi.org/10.1177/0391398818777697.

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Purpose: Numerical flow analysis (computational fluid dynamics) in combination with the prediction of blood damage is an important procedure to investigate the hemocompatibility of a blood pump, since blood trauma due to shear stresses remains a problem in these devices. Today, the numerical damage prediction is conducted using unsteady Reynolds-averaged Navier–Stokes simulations. Investigations with large eddy simulations are rarely being performed for blood pumps. Hence, the aim of the study is to examine the viscous shear stresses of a large eddy simulation in a blood pump and compare the results with an unsteady Reynolds-averaged Navier–Stokes simulation. Methods: The simulations were carried out at two operation points of a blood pump. The flow was simulated on a 100M element mesh for the large eddy simulation and a 20M element mesh for the unsteady Reynolds-averaged Navier-Stokes simulation. As a first step, the large eddy simulation was verified by analyzing internal dissipative losses within the pump. Then, the pump characteristics and mean and turbulent viscous shear stresses were compared between the two simulation methods. Results: The verification showed that the large eddy simulation is able to reproduce the significant portion of dissipative losses, which is a global indication that the equivalent viscous shear stresses are adequately resolved. The comparison with the unsteady Reynolds-averaged Navier–Stokes simulation revealed that the hydraulic parameters were in agreement, but differences for the shear stresses were found. Conclusion: The results show the potential of the large eddy simulation as a high-quality comparative case to check the suitability of a chosen Reynolds-averaged Navier–Stokes setup and turbulence model. Furthermore, the results lead to suggest that large eddy simulations are superior to unsteady Reynolds-averaged Navier–Stokes simulations when instantaneous stresses are applied for the blood damage prediction.
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Smith, M. J., and A. Moushegian. "Dual-solver hybrid computational approaches for design and analysis of vertical lift vehicles." Aeronautical Journal 126, no. 1295 (2021): 187–208. http://dx.doi.org/10.1017/aer.2021.108.

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AbstractThe cost of Reynolds-Averaged Navier-Stokes simulations can be restrictive to implement in aeromechanics design and analysis of vertical lift configurations given the cost to resolve the flow on a mesh sufficient to provide accurate aerodynamic and structural loads. Dual-solver hybrid methods have been developed that resolve the configuration and the near field with the Reynolds-Averaged Navier-Stokes solvers, while the wake is resolved with vorticity-preserving methods that are more cost-effective. These dual-solver approaches can be integrated into an organisation’s workflow to bridge the gap between lower-fidelity methods and the expensive Reynolds-Averaged Navier-Stokes when there are complex physics present. This paper provides an overview of different dual-solver hybrid methods, coupling approaches, and future efforts to expand their capabilities in the areas of novel configurations and operations in constrained and turbulent environments.
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Netzer, Corinna, Lars Seidel, Frédéric Ravet, and Fabian Mauss. "Assessment of the validity of RANS knock prediction using the resonance theory." International Journal of Engine Research 21, no. 4 (2019): 610–21. http://dx.doi.org/10.1177/1468087419846032.

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Following the resonance theory by Bradley and co-workers, engine knock is a consequence of an auto-ignition in the developing detonation regime. Their detonation diagram was developed using direct numerical simulations and was applied in the literature to engine knock assessment using large eddy simulations. In this work, it is analyzed if the detonation diagram can be applied for post-processing and evaluation of predicted auto-ignitions in Reynolds-averaged Navier–Stokes simulations even though the Reynolds-averaged Navier–Stokes approach cannot resolve the fine structures resolved in direct numerical simulations and large eddy simulations that lead to the prediction of a developing detonation. For this purpose, an engine operating point at the knock limit spark advance is simulated using Reynolds-averaged Navier–Stokes and large eddy simulations. The combustion is predicted using the G-equation and the well-stirred reactor model in the unburnt gases based on a detailed gasoline surrogate reaction scheme. All the predicted ignition kernels are evaluated using the resonance theory in a post-processing step. According to the different turbulence models, the predicted pressure rise rates and gradients differ. However, the predicted ignition kernel sizes and imposed gas velocities by the auto-ignition event are similar, which suggests that the auto-ignitions predicted by Reynolds-averaged Navier–Stokes simulations can be given a meaningful interpretation within the detonation diagram.
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Frazza, Loïc, Adrien Loseille, Alain Dervieux, and Frédéric Alauzet. "Nonlinear corrector for Reynolds‐averaged Navier‐Stokes equations." International Journal for Numerical Methods in Fluids 91, no. 11 (2019): 557–85. http://dx.doi.org/10.1002/fld.4764.

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Tesi sul tema "Équations de Reynolds-Averaged Navier Stokes"

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Frazza, Loïc. "3D anisotropic mesh adaptation for Reynolds Averaged Navier-Stokes simulations." Thesis, Sorbonne université, 2018. http://www.theses.fr/2018SORUS423.

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Nous montrons dans cette thèse la capacité des schémas numériques modernes à simuler des écoulements turbulents sur des maillages totalement non-structurés générés automatiquement à l’aide de méthodes adaptatives. Nous détaillons le développement de différentes versions du modèle de Spalart-Allmaras ainsi que les choix numériques garantissant une robustesse suffisante du solver pour ne pas nécessiter de couche limite structurée. Nous introduisons en suite l’analyse d’erreur nécessaire pour proposer different estimateurs d’erreur à la base de l’optimisation de maillage. Cette méthodologie est testée sur différents cas tests d’aérodynamique externe et de turbomachines et comparée aux méthodes traditionnelles de géneration de maillage. Nous montrons ainsi la capacité des méthodes d’adaptation de maillage à générer automatiquement des maillages adaptés optimaux pour les simulations RANS autour de géométries réalistes et complexes<br>The fast and reliable simulation of turbulent flow using Reynolds Averaged Navier Stokes (RANS) models is a major financial issue for many industries. With the increasing complexity of geometries and simulated flows, as well as requirements in terms of fidelity, the generation of appropriate meshes has become a key link in the chain of computation. We show in this thesis the ability of modern numerical schemes to simulate turbulent flows on fully unstructured meshes generated automatically using mesh adaptation methods. We present the implementation of different versions of the Spalart-Allmaras model as well as the numerical choices guaranteeing a sufficient robustness of the solver in order to not require a structured boundary layer. We then introduce the error analysis necessary to propose different error estimators for mesh optimization. This methodology is tested on various external aerodynamic and turbomachinery test cases and compared to traditional mesh generation methods. We show the ability of mesh adaptation methods to automatically generate optimal mesh sizes for RANS simulations on realistic and complex geometries
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Zhang, Yunzh. "Contribution à la résolution des équations de Navier-Stokes par la méthode des équations intégrales." Palaiseau, Ecole polytechnique, 2003. http://www.theses.fr/2003EPXX0006.

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Assemien, Ahiko. "Comportement asymptotique des équations de Navier-Stokes pour des écoulements de faible épaisseur." Lyon 1, 1993. http://www.theses.fr/1993LYO10010.

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Dans ce travail nous nous interessons au comportement asymptotique des equations de navier-stokes en regime stationnaire, dans des domaines avec une faible epaisseur. Notre domaine d'etude est constitue de la jonction d'un film mince et d'un domaine appele cavite de grande dimension devant celle du film mince. Dans une premiere partie nous considerons des conditions aux limites non homogenes en vitesse. Grace a des inegalites du type inclusions de sobolev tenant compte de la non-isotropie du domaine nous montrons que dans le film mince les effets d'inertie n'interviennent pas dans l'equation verifiee par le premier terme du developpement asymptotique de la pression cette equation etant l'equation de reynolds classique pour les films minces. On met en evidence l'influence des effets d'inertie dans le deuxieme terme du developpement et pour un choix judicieux des conditions aux limites nous obtenons des resultats de convergence au deuxieme ordre. Dans la cavite la vitesse limite est nulle et la pression limite constante. On prouve que la pression limite n'admet pas de saut a l'interface des deux domaines. Dans une deuxieme partie nous considerons le probleme de la lubrification hydrostatique avec conditions aux limites homogenes en vitesse sur une partie de la frontiere et conditions aux limites en pression sur l'autre partie. On trouve dans le film mince le meme type d'equations. Dans la cavite les equations sont celles de stokes, d'euler ou de navier-stokes. Dans la derniere partie nous presentons des resultats numeriques relatifs au probleme de la lubrification hydrodynamique
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Ravalason, William. "Résolution numérique des équations de Navier-Stokes pour les écoulements transsoniques autour d'arrière-corps droits." Lille 1, 1985. http://www.theses.fr/1985LIL10117.

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La méthode retenue est fondée sur la résolution, par un schéma implicite, des équations de Navier-Stokes instationnaires bidimensionnelles. Les applications de cette méthode concernent l'écoulement autour d'un projectile de type ogive-cylindre. Dans un premier temps, on examine le cas des nombres de Reynolds modérés et, dans un deuxième temps, celui des grandes valeurs du nombre de Reynolds, la turbulence étant alors prise en compte par l'utilisation d'un modèle algébrique de type longueur de mélange.
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Wakrim, Mohamed. "Analyse numérique des équations de Navier-Stokes incompressibles et simulations dans des domaines axisymétriques." Saint-Etienne, 1993. http://www.theses.fr/1993STET4015.

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Dans cette thèse, on a développé une méthode numérique pour la simulation des écoulements de fluides à nombre de Reynolds élevé, utilisant deux types d'éléments finis. On a établi la convergence de l'algorithme d'Uzawa en formulation de Petrov-Galerkin et on a étudié l'élément fini de Crouzeix-Raviart en formulation de Petrov-Galerkin. Pour finir, on a construit un préconditionneur du CGS pour une formulation couplée
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Guilmineau, Emmanuel. "Contribution a la prediction du decrochage sur des ailes en incidence au moyen des equations de navier-stokes-reynolds." Nantes, 1995. http://www.theses.fr/1995NANT2097.

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Ce travail concerne la resolution numerique des equations de navier-stokes, ecrites sous forme conservative, pour un ecoulement de fluide incompressible. La reconstruction des flux est realisee par la methode cpi (consistent physical interpolation) qui s'applique aussi bien aux flux de masse qu'a ceux de quantite de mouvement. Des comparaisons avec des donnees experimentales sont systematiquement realisees. Les premieres applications sont la mise en impulsion d'un ecoulement laminaire autour d'un cylindre de section circulaire et d'un profil d'aile naca 0012. De tels problemes sont souvent utilises comme cas tests numeriques pour des etudes d'ecoulement instationnaire produisant une separation massive. Ensuite, on s'interesse a la prediction d'un ecoulement laminaire autour d'un profil d'aile naca 0012 en oscillations de tangage. Une autre application envisagee est la prediction d'ecoulements turbulents pour etudier les caracteristiques du decrochage de profils bidimensionnels a incidence fixe. Trois modeles de turbulence sont utilises: le modele baldwin-lomax, le modele baldwin-barth et le modele k-sst. Les profils d'aile etudies sont: le profil naca 4412 a son incidence de portance maximale, 13. 87, le profil as 240 ou profil b pour deux incidences: 8 et 19 et le profil ga(w)-1 pour les incidences suivantes: 4. 17, 14. 4 et 20. 05. Pour achever cette etude, l'ecoulement turbulent autour d'un profil naca 0012 en mouvement de tangage est considere avec plusieurs modeles de turbulence. Dans tous les cas, le modele k-sst donne de meilleurs resultats de portance et moment. Ce travail se termine par l'etude d'un ecoulement tridimensionnel turbulent autour d'une aile, en incidence, de section naca 0015 et d'envergure finie
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Kahil, Yacine. "Simulation des grandes échelles d'écoulements turbulents autour de cylindres circulaires à un nombre de Reynolds sous critique." Paris 6, 2011. http://www.theses.fr/2011PA066631.

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La thèse présente des études numériques avec analyse approfondie d'écoulements turbulents autour d'un ou plusieurs cylindres sur différentes configurations illustratives d'applications industrielles. L'objectif est de comprendre le comportement de l'écoulement et d'expliquer les phénomènes physiques qui apparaissent dans certaines configurations. A l'aide de la technique de la simulation des grandes échelles (LES), les champs instantanés de l'écoulement et les forces exercées sur les cylindres sont calculés. En variant la distance entre le centre des cylindres, plusieurs topologies de sillage apparaissent. Les simulations ont montré que pour les petits espacements, les configurations se comportent quasiment comme un corps unique. Cependant, pour les rapports intermédiaires, des instabilités apparaissent avec changement de comportement de l'écoulement et aussi des échappements tourbillonnaires qui auraient un grand effet sur les fluctuations des structures. Le but de notre travail est de définir les causes de ces instabilités et le moment de leur apparition. Pour les grands espacements, les structures se comportent comme un seul cylindre avec certaines différences pour ceux situés dans le sillage des cylindres en amont. En plus, l'influence de l'espacement sur les changements de mode et les structures qui en sont responsables sont présentée en détail. Les données obtenues dans cette thèse permettront d'une part d'aborder la configuration de faisceaux de tube avec un degré de confiance plus élevé. D'autre part, une base de données sera créée et mise à disposition de la communauté scientifique pour la validation des codes de calcul ou la compréhension approfondie des phénomènes physiques en jeu
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Guenot, Damien. "Simulation des effets instationnaires à grande échelle dans les écoulements décollés." École nationale supérieure de l'aéronautique et de l'espace (Toulouse ; 1972-2007), 2004. http://www.theses.fr/2004ESAE0009.

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Le calcul des écoulements turbulents décollés est un des enjeux majeurs de l’aérodynamique numérique. Différentes méthodes existent : résolution des équations moyennées stationnaires, instationnaires (RANS/URANS), ou Simulation des Grandes Échelles (SGE). La méthode hybride Detached Eddy Simulation (DES) semble bien adaptée : elle utilise un modèle unique qui se comporte près des parois comme un modèle URANS (limite le coût de calcul), et loin comme une SGE (décrit mieux les écoulements hors équilibre). Les calculs de plaque plane montrent la nécessité de calculer les zones attachées en mode URANS. Pour le profil en décrochage, différents paramètres (maillage, envergure, formulation en mode SGE) sont testés. On obtient une meilleure prévision de la portance et de la traînée par rapport à l’URANS. Le cas de la marche descendante montre les limites de la DES. La géométrie pose le problème de la couche limite amont épaisse où les structures turbulentes sont absentes (traitée en URANS).
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Chegroun, Nouara. "Etude numérique des actions hydrodynamiques sur une sphère en translation et rotation dans la gamme des nombres de Reynolds inferieurs à 50." Vandoeuvre-les-Nancy, INPL, 1992. http://www.theses.fr/1992INPL122N.

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Dans le but de déterminer les coefficients de trainée, de portance et de couple d'une sphère animée d'un mouvement de translation et de rotation simultanées, on propose une résolution numérique des équations de Navier-Stokes au moyen d'une méthode de correction de pression appliquée à un maillage non uniforme construit sur des coordonnées sphériques. L'étude est limitée au régime stationnaire, dans le domaine des nombres de Reynolds inferieurs à 50, qui sont ceux que l'on rencontre le plus fréquemment en mécanique des suspensions. Les résultats obtenus apportent des informations originales, complétant utilement les rares connaissances existantes dans cette gamme de nombres de Reynolds intermédiaires
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Dauby, Davy. "Simulation d'écoulements cavitants par résolution numérique des équations de Navier-Stokes en moyenne de reynolds : application à la cavitation de tourbillon d'extrémité." Nantes, 2007. http://www.theses.fr/2007NANT2141.

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Le présent travail de thèse s'inscrit dans une logique d'intégration de nouveaux phénomènes physiques dans les solveurs Navier-Stokes dont la maturité atteinte aujourd'hui leur permet d'appréhender de nombreux domaines de la physique autres que la mécanique des fluides. Le modèle de cavitation de type production-destruction, intégré dans un solveur Navier-Stokes utilisant une méthode de type Volumes-Finis non structurés, est présenté. Les différentes méthodes numériques pour mener de façon robuste le calcul d'écoulement cavitans sont exposées. On s'attarde notamment sur les difficultés intrinsèques au modèle de cavitation employé et sur l'influence de ses paramètres dans le cas d'une poche de cavitation attachée au bord d'attaque d'un profil d'aile bidimensionnel. Dans le cadre d'une thématique connexe de la cavitation en hydrodynamique, on s'intéresse à la capture, par deux méthodes de raffinement local; du tourbillon d'extrémité généré par un profil d'aile tridimensionnel de forme en plan elliptique. Enfin l'application tridimensionnel du modèle de cavitation sur une hélice en rotation en eau calme est proposée<br>This present PhD work is part of the new trend of implementation of new physical phenomena in Navier-Stokes solver , which have reached a maturity that eneables them to deal with problems in many fields of physics other than fluid mechanics. The production-desctruction cavitation model employed in this work, implemented in a Navier-Stokes solover bases on a fully unstructured Finite Volume method is presented. The various numerical methods employed to run computations of cavitating flows in a robust way are exposed. The emphasis is on the intrinsic diffulties of the cavitation model and on the influence of its parmeters in the case of a leading ede cavity sheet on a two dimensional hydrofoil. In a theme closely related to hydrodynamic cavitation, we focus on the capturing, using two local refinement method of a tip-vortex generated by a tree-dimensional elliptic hydrofoil. Finally, a three-dimensional application of the cavitation model on a propeller rotating in open water is proposed
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Libri sul tema "Équations de Reynolds-Averaged Navier Stokes"

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Mavriplis, Dimitri J. A three dimensional multigrid Reynolds-averaged Navier-Stokes solver for unstructured meshes. Institute for Computer Applications in Science and Engineering, 1994.

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2

R, Laflin K., and United States. National Aeronautics and Space Administration., eds. Reynolds-averaged Navier-Stokes simulations of two partial-span flap wing experiments. American Institute of Aeronautics and Astronautics, 1998.

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3

R, Laflin K., and United States. National Aeronautics and Space Administration., eds. Reynolds-averaged Navier-Stokes simulations of two partial-span flap wing experiments. American Institute of Aeronautics and Astronautics, 1998.

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4

R, Laflin K., and United States. National Aeronautics and Space Administration., eds. Reynolds-averaged Navier-Stokes simulations of two partial-span flap wing experiments. American Institute of Aeronautics and Astronautics, 1998.

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5

Lamarre, Francois. One-equation turbulence models for the solution of the Reynolds-averaged equations. Princeton University, School of Engineering and Applied Science, Dept. of Mechanical and Aerospace Engineering, 1992.

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6

Chaussee, D. S. High-speed flow calculations past 3-D configurations based on the Reynolds averaged Navier-Stokes equations. National Aeronautics and Space Administration, Ames Research Center, 1988.

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Chaussee, D. S. High-speed flow calculations past 3-D configurations based on the Reynolds averaged Navier-Stokes equations. National Aeronautics and Space Administration, Ames Research Center, 1988.

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8

United States. National Aeronautics and Space Administration., ed. Reynolds-averaged Navier-Stokes studies of low Reynolds number effects on the losses in a low pressure turbine. National Aeronautics and Space Administration, 1996.

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9

United States. National Aeronautics and Space Administration., ed. Reynolds-averaged Navier-Stokes studies of low Reynolds number effects on the losses in a low pressure turbine. National Aeronautics and Space Administration, 1996.

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10

United States. National Aeronautics and Space Administration., ed. Reynolds-averaged Navier-Stokes studies of low Reynolds number effects on the losses in a low pressure turbine. National Aeronautics and Space Administration, 1996.

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Capitoli di libri sul tema "Équations de Reynolds-Averaged Navier Stokes"

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Kajishima, Takeo, and Kunihiko Taira. "Reynolds-Averaged Navier–Stokes Equations." In Computational Fluid Dynamics. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-45304-0_7.

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Wang, Tongguang, Wei Zhong, Yaoru Qian, and Chengyong Zhu. "Reynolds-Averaged Navier–Stokes Method for Wind Turbine Simulations." In Wind Turbine Aerodynamic Performance Calculation. Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-99-3509-3_11.

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3

Rautaheimo, Patrik, Timo Siikonen, and Antti Hellsten. "Diagonalization of the Reynolds-averaged Navier-Stokes equations with the Reynolds-stress Turbulence Model." In Notes on Numerical Fluid Mechanics (NNFM). Vieweg+Teubner Verlag, 1996. http://dx.doi.org/10.1007/978-3-322-89838-8_32.

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4

Deville, Michel O. "Turbulence." In An Introduction to the Mechanics of Incompressible Fluids. Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-031-04683-4_9.

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Abstract (sommario):
AbstractThe Reynolds decomposition and statistical averaging of velocity and pressure generate the Reynolds averaged Navier–Stokes (RANS) equations. The closure problem is solved by the introduction of a turbulence constitutive equation. Several linear turbulence models are presented in the RANS framework: $$K-\varepsilon , K-\omega $$ K - ε , K - ω . The solution of the RANS equations for the turbulent channel flow is elaborated giving the celebrated logarithmic profile. Non-linear models are built on the anisotropy tensor and the incorporation of the concept of integrity bases. The chapter ends with the theory of large eddy simulations with a few up-to-date models: dynamic model, approximate deconvolution method.
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5

Allen, Alexander, Michail Iatrou, Alexander Pechloff, and Boris Laschka. "Computation of Delta Wing Flap Oscillations with a Reynolds-Averaged Navier-Stokes Solver." In New Results in Numerical and Experimental Fluid Mechanics V. Springer Berlin Heidelberg, 2006. http://dx.doi.org/10.1007/978-3-540-33287-9_11.

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Morán-López, J. Tiberius, Oleg Schilling, and James P. Holloway. "Reynolds-Averaged Navier–Stokes Modeling of Reshocked Richtmyer–Meshkov Instability Experiments and Simulations." In 29th International Symposium on Shock Waves 2. Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-16838-8_40.

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Hughes, Thomas J. R., Kenneth Jansen, and Guillermo Hauke. "Applications of the Finite Element Method to the Reynolds-Averaged Navier-Stokes Equations." In Notes on Numerical Fluid Mechanics (NNFM). Vieweg+Teubner Verlag, 1998. http://dx.doi.org/10.1007/978-3-322-89859-3_24.

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Jianhua, Xu, Song Wenping, and Han Zhonghua. "Calculation of Aerodynamic Performance of Propellers at Low Reynolds Number Based on Reynolds-Averaged Navier-Stokes Equations Simulation." In Computational Fluid Dynamics 2008. Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-642-01273-0_34.

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Knight, Doyle D. "Simulation of Shock Wave-Turbulent Boundary Layer Interactions Using the Reynolds-Averaged Navier-Stokes Equations." In ICASE/LaRC Interdisciplinary Series in Science and Engineering. Springer Netherlands, 1999. http://dx.doi.org/10.1007/978-94-011-4724-8_16.

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10

Li, Ze, DongMei Yang, GuiSheng Yin, Jun Shi, and JianNing Gen. "Numerical Simulation of a Damaged Salvage Ship in Beam Wave with Reynolds-Averaged Navier-Stokes Method." In Lecture Notes in Civil Engineering. Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-99-4291-6_73.

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Atti di convegni sul tema "Équations de Reynolds-Averaged Navier Stokes"

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Cross, Philip, Joachim Hodara, and Marilyn Smith. "Evaluation of Transitional Effects in Rotorcraft Applications." In Vertical Flight Society 72nd Annual Forum & Technology Display. The Vertical Flight Society, 2016. http://dx.doi.org/10.4050/f-0072-2016-11385.

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Abstract (sommario):
Transition in computational simulations is still an emerging area of algorithm development for rotorcraft applications. It, along with turbulence modeling, is assumed to be the source of errors in many numerical analyses. To explore the influence of transition, two transition methods are analyzed across different configurations of interest to rotorcraft. The Langtry cross flow model for Reynolds-Averaged Navier-Stokes (RANS) solvers and a consistent transition approach to the Georgia Tech hybrid Reynolds-Averaged Navier-Stokes and Large Eddy Simulation (RANS-LES or HRLES) are evaluated. The configurations include a prolate spheroid, a rotor-body interaction (ROBIN) generic model fuselage, and a two-dimensional yawed wing. The solutions indicate the importance of not only transition, but also crossflow transition on rotor and fuselage aerodynamic behavior.
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Smith, Luke, Marilyn Smith, Andrew Lind, Anya Jones, and Kevin Jacobson. "Experimental and Computational Investigation of a Linearly Pitching NACA 0012 in Reverse Flow." In Vertical Flight Society 72nd Annual Forum & Technology Display. The Vertical Flight Society, 2016. http://dx.doi.org/10.4050/f-0072-2016-11390.

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The reverse flow region of a high advance ratio rotor is modeled using a linearly pitching semi-infinite NACA 0012 blade section in a constant reverse flow freestream. A coupled experimental-numerical approach is used to investigate the instantaneous and ensemble-averaged unsteady aerodynamics. Two pitch cases were considered: 0° ≤ αrev ≤ 20° (i.e., high pitch) and 5° ≤ αrev ≤ 15° (i.e., low pitch). Transient flow phenomena were characterized experimentally using time-resolved particle image velocimetry and unsteady pressure measurements. In the high pitch case, the measured velocity field was dominated by a periodic primary dynamic stall vortex, a trailing edge vortex, and several weak secondary vortices. All three flow structures were present in the Hybrid Reynolds-Averaged Navier Stokes Large Eddy Simulation (tHRLES), while only the primary dynamic stall vortex and trailing edge vortex were present in Unsteady Reynolds-Averaged Navier Stokes (URANS) solver. For the low pitch case, the experimentally measured velocity field was instead characterized by a series of weak vortices that rapidly along the chord; these aperiodic vortices were present in the tHRLES simulation but absent from URANS simulation. The experimental and numerical results suggest that initial pitch angle and pitch rate are driving forces in the character of a NACA 0012 undergoing linear pitching in a constant reverse flow freestream. The comparisons between experimental and numerical flow fields and integrated unsteady airloads show promise in the ability of the Hybrid Reynolds-Averaged Navier Stokes Large Eddy Simulation (tHRLES) code to accurately capture the nonlinear transients observed experimentally.
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3

Zhang, H., C. Bachman, and H. Fasel. "Reynolds-averaged Navier-Stokes calculations of unsteady turbulent flow." In 38th Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-143.

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Gherman, George Bogdan, Ion Malael, Mihai Mihaescu, and Ionut Porumbel. "Jet pump optimization through Reynolds averaged Navier-Stokes Simulation Analysis." In 22nd AIAA Computational Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-2610.

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Chyczewski, Thomas S. "Steady Reynolds Averaged Navier Stokes Equation-Based Buffet Loads Estimation." In 34th AIAA Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-4045.

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Coimbra, Alain, and Luís Fernando Figueira da Silva. "REYNOLDS-AVERAGED NAVIER-STOKES MODELLING OF TURBULENT LEAN PREMIXED COMBUSTOR." In 25th International Congress of Mechanical Engineering. ABCM, 2019. http://dx.doi.org/10.26678/abcm.cobem2019.cob2019-0443.

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Hu, Xiaohan, George P. Huang, Paul Durbin, and Xiang I. Yang. "Compressibility Corrections for Two-Equation Reynolds-Averaged Navier-Stokes Models." In AIAA SCITECH 2025 Forum. American Institute of Aeronautics and Astronautics, 2025. https://doi.org/10.2514/6.2025-2749.

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Barrouillet, Benjamin, Eric Laurendeau, and Hong Yang. "Optimized cross flow transition model for Reynolds Averaged Navier Stokes applications." In AIAA AVIATION 2021 FORUM. American Institute of Aeronautics and Astronautics, 2021. http://dx.doi.org/10.2514/6.2021-2714.

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Liu, Xin, Liangzhong Chen, Xiaogang Deng, and Meiliang Mao. "Assessment of CHANT v1.0 for Calculating Reynolds-Averaged Navier-Stokes Equations." In 38th Fluid Dynamics Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-3990.

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Freno, Brian, Thomas Brenner, and Paul Cizmas. "Proper Orthogonal Decomposition Applied to the Reynolds-Averaged Navier--Stokes Equations." In 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-314.

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Rapporti di organizzazioni sul tema "Équations de Reynolds-Averaged Navier Stokes"

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Gorski, Joseph J., and Gregory M. Buley. Force and Moment Calculations of an Appendage Using the Reynolds Averaged Navier-Stokes Equations. Defense Technical Information Center, 1998. http://dx.doi.org/10.21236/ada360510.

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2

Edwards, Jack R. Large-Eddy/Reynolds-Averaged Navier-Stokes Simulation of Shock-Train Development in a Coil-Laser Diffuser. Defense Technical Information Center, 2014. http://dx.doi.org/10.21236/ada612441.

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Laskowski, Gregory Michael. Predictions of flow through an isothermal serpentine passage with linear eddy-viscosity Reynolds Averaged Navier Stokes models. Office of Scientific and Technical Information (OSTI), 2005. http://dx.doi.org/10.2172/875612.

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4

Patel, V. C., H. C. Chen, and S. Ju. Ship Stern and Wake Flows: Solutions of the Fully-Elliptic Reynolds-Averaged Navier-Stokes Equations and Comparisons with Experiments. Defense Technical Information Center, 1988. http://dx.doi.org/10.21236/ada199377.

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Edwards, Jack R. Simulation of Transient Dynamics of Shock Wave Boundary Layer Interactions Using Hybrid Large-Eddy/Reynolds-Averaged Navier-Stokes Models. Defense Technical Information Center, 2007. http://dx.doi.org/10.21236/ada482276.

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Rahai, Hamid, and Assma Begum. Numerical Investigations of Transient Wind Shear from Passing Vehicles Near a Road Structure (Part I: Unsteady Reynolds-Averaged Navier-Stokes Simulations). Mineta Transportation Institute, 2021. http://dx.doi.org/10.31979/mti.2020.1933.

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Abstract (sommario):
In this research, the authors performed unsteady numerical simulations of a moving Ahmed body under a freeway overpass at different distances from the bridge columns in order to evaluate transient wind shear and the wind load on these columns. Results have shown that when the vehicle is at 0.75W distance from the bridge columns, an unsteady wind speed of up to 24 m/s is observed at the columns with a pressure coefficient difference of 0.9. Here W is the width of the vehicle. These results indicate with an appropriate system for harnessing these wind energy potentials, significant renewable electric power could be generated with zero carbon footprint.
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Zheng, Wanzheng, and Jason Merret. Aerodynamic Survey of Novel eVTOL Configuration Using SU2. Illinois Center for Transportation, 2022. http://dx.doi.org/10.36501/0197-9191/22-014.

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This report summarizes computational fluid dynamics (CFD) results of electric vertical takeoff and landing (eVTOL) geometries using the SU2 Reynolds-averaged Navier-Stokes (RANS) solver. Geometries were generated based on the Smart Transportation Infrastructure Initiative (STII) Rappor 15th iteration with various rotor-installment solutions. It was found that although open rotors installed on an underwing pylon were superior to shrouded rotors installed in a canoe, the canoe configuration would provide more potential for improvement, and using a canoe door to cover the first rotor opening would reduce the drag experienced by the canoe case below that upon the rod case. Rotor doors were found to be most efficient in reducing drag of the canoe case: Average drag reduction with covering the first rotor and all rotors was 66 and 165 counts, respectively. Changing rotor distributions along the chordwise direction had minimal impact on drag reduction, and placing rotors along the spanwise direction was not advised due to the increase of the projected frontal area. Increasing canoe chord length did not have significant impact on drag reduction; and if rotor doors were implemented, increasing canoe size had negative impact on drag. Rounding rotor edges did not change the aerodynamic performance of the canoe case but promotes vertical air intake when running lifting fans. Drag received by the canoe parabolically correlated to rotor diameter, with 126 counts of drag if the rotor diameter was 0 and 377 counts if the rotor diameter was 2.95 ft. Fuselage and tail added an average 179 counts of drag, and thus the aforementioned differences were still significant in the scale of aerodynamic properties of the full configuration.
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