Дисертації з теми "Ingestion de couche limite"
Оформте джерело за APA, MLA, Chicago, Harvard та іншими стилями
Ознайомтеся з топ-50 дисертацій для дослідження на тему "Ingestion de couche limite".
Біля кожної праці в переліку літератури доступна кнопка «Додати до бібліографії». Скористайтеся нею – і ми автоматично оформимо бібліографічне посилання на обрану працю в потрібному вам стилі цитування: APA, MLA, «Гарвард», «Чикаго», «Ванкувер» тощо.
Також ви можете завантажити повний текст наукової публікації у форматі «.pdf» та прочитати онлайн анотацію до роботи, якщо відповідні параметри наявні в метаданих.
Переглядайте дисертації для різних дисциплін та оформлюйте правильно вашу бібліографію.
Solorzano, Flores Hector. "Understanding and prediction of flow physics on a boundary layer ingestion air intake for a commercial aircraft." Electronic Thesis or Diss., Institut polytechnique de Paris, 2023. http://www.theses.fr/2023IPPAX093.
The thesis investigates the physical phenomena arising from the interaction between a Boundary Layer Ingestion (BLI) engine intake and the fuselage under off-design conditions for a commercial aircraft. A buried BLI intake geometry on a flat plate is employed. The study involves both numerical and experimental analyses, characterizing the steady and unsteady flow behavior. The predictive capability of various CFD turbulence models, RANS and hybrid RANS/LES, is assessed and compared with wind tunnel test data. The flow distortion at the Aerodynamic Interface Plane (AIP), the main drawback of using a BLI engine, is quantified. Different distortion criteria used in the industry are examined, highlighting their strengths and weaknesses. Finally, the results of this thesis provide a deeper understanding of the flow behavior of this type of configuration, as well as the potential and limitations of the numerical methods applied. The results of the thesis may also serve as a basis for reflection on the use of active flow control to optimize the benefit of the BLI concept while respecting the multiple design constraints, especially related to the engine intake operation outside cruise conditions and the physical integration of the engine on the aircraft
Glikson, Fabienne. "Couche limite sur paroi rugueuse." Toulouse, ENSAE, 1996. http://www.theses.fr/1996ESAE0003.
Frangi, Jean-Pierre. "Dynamique de la couche limite de surface sahélienne." Toulouse 3, 1988. http://www.theses.fr/1988TOU30247.
PERLAT, JEAN-PHILIPPE. "Modelisation et calcul parallele d'une couche limite cinetique." Paris 6, 1998. http://www.theses.fr/1998PA066678.
Aguilar, Jean-Christophe. "Optimisation de formes hydrodynamiques : Couche limite intrinsèque tridimensionnelle." Paris, ENMP, 1996. http://www.theses.fr/1996ENMP0834.
Frangi, Jean-Pierre. "Dynamique de la couche limite de surface sahélienne." Grenoble 2 : ANRT, 1988. http://catalogue.bnf.fr/ark:/12148/cb37613677j.
Rouault, Mathieu. "Modélisation numérique d'une couche limite unidimensionnelle stationnaire d'embruns." Aix-Marseille 2, 1989. http://www.theses.fr/1989AIX22028.
Lahrichi, Mohamed Seddik. "Etude expérimentale de couches limites cinématiques sur une aube de turbine aéronautique à grande échelle." Ecully, Ecole centrale de Lyon, 1994. http://www.theses.fr/1994ECDL0049.
Moursali, El Mostafa. "Etude expérimentale d'une couche limite eau-air a bulles se développant sur une plaque plane verticale." Ecully, Ecole centrale de Lyon, 1993. http://www.theses.fr/1993ECDL0018.
Ferrey, Paul. "Modèles aux tensions de Reynolds avec prise en compte de l’intermittence de frontière." Poitiers, 2004. http://www.theses.fr/2004POIT2331.
The goal of this PhD thesis is to optimise a Reynolds stress model. Some constraints are applied to the length scale transport equation in order to take into account the effect of a pressure gradient on the structure of the boundary layer. This leads us to revisit the analysis of the behaviour of turbulence models at the vicinity of a free stream edge. The behaviour is different from what has been assumed before as the expected power law solution is contained in a more complex solution. This study proved that the constraints for the free stream edge are incompatible with the other constraints. The intermittent character of the free stream edge is taken into account in order to unlink the behaviour of the model at the free stream edge from its behaviour in fully turbulent regions. The model deduced from this analysis fulfils all the constraints and is calibrated on free shear flows and boundary layers where the constraints significantly improve the quality of results
Chosson, Frédérick. "Transfert radiatif dans les nuages de couche limite hétérogènes." Phd thesis, Université Paul Sabatier - Toulouse III, 2006. http://tel.archives-ouvertes.fr/tel-00179771.
Trijoulet, Alexandre. "Étude expérimentale de couche limite turbulente sur paroi rugueuse." École nationale supérieure de l'aéronautique et de l'espace (Toulouse ; 1972-2007), 1999. http://www.theses.fr/1999ESAE0026.
Boutouili, Mohieddine. "Etude statistique expérimentale d'une combustion turbulente en couche limite." Poitiers, 1988. http://www.theses.fr/1988POIT2336.
Carvin, Christian. "Etude expérimentale d'une couche limite turbulente supersonique fortement chauffée." Aix-Marseille 2, 1988. http://www.theses.fr/1988AIX22006.
SCHWEITZER, FRANCIS. "Chimie multiphasique tropospherique - application a la couche limite marine." Université Louis Pasteur (Strasbourg) (1971-2008), 1999. http://www.theses.fr/1999STR13047.
Arnoux, Joël. "Champ turbulent d'une couche limite tridimensionnelle sur paroi mobile." Aix-Marseille 2, 1986. http://www.theses.fr/1986AIX22024.
Monavon, Arnault. "Etude d'une couche limite instationnaire sur une paroi déformable." Paris 6, 1986. http://www.theses.fr/1986PA066369.
Arnoux, Joël. "Champ turbulent d'une couche limite tridimensionnelle sur paroi mobile." Grenoble 2 : ANRT, 1986. http://catalogue.bnf.fr/ark:/12148/cb37595546z.
Aymer, de la Chevalerie Dominique. "Interaction onde de choc-couche limite modélisation et calcul." Grenoble 2 : ANRT, 1986. http://catalogue.bnf.fr/ark:/12148/cb37595581g.
Monavon, Arnault. "Etude d'une couche limite instationnaire sur une paroi déformable." Grenoble 2 : ANRT, 1986. http://catalogue.bnf.fr/ark:/12148/cb37599782b.
Boutouili, Mohleddine. "Etude statistique expérimentale d'une combustion turbulente en couche limite." Grenoble 2 : ANRT, 1988. http://catalogue.bnf.fr/ark:/12148/cb376122687.
Carvin, Christian. "Etude expérimentale d'une couche limite turbulente supersonique fortement chauffée." Grenoble 2 : ANRT, 1988. http://catalogue.bnf.fr/ark:/12148/cb376124930.
Bonne, Nicolas. "Stabilité de l'intéraction onde de choc/ couche limite laminaire." Thesis, Université Paris-Saclay (ComUE), 2018. http://www.theses.fr/2018SACLX025/document.
The shock wave boundary layer (BL) interaction phenomenon is ubiquitous in aerodynamic. In general this interaction generates some low frequency oscillations which can be disastrous for the machines. The typical example is the buffet phenomenon on an airfoil in transonic conditions. Buffet is dangerous since its low frequency can excite the structural modes of the airfoil and break it. The phenomenology has been wildly studied when the incoming BL is turbulent. These studies have derived several credible scenarii and efficient methodologies to capture its dynamic, especially the stability analysis tools on an averaged turbulent flow (RANS). However laminar technologies, the use of laminar BL to reduce the fuel consumption of planes, represent a new scientific challenge on this problematic. In fact, the physic of the interaction is importantly impacted by the laminar nature of the BL especially because of its weak resilience to an adversed pressure gradient and of the transition to turbulence.The thesis deals with the methodologies for the stability analysis on a RANS base flow in the case of a laminar BL. The originality and the contribution of this work have been to take into account a transition criteria in the linearised dynamic on a RANS base flow. The model used (RANS and transition) have then been linearized in order to make a stability analysis which take into account all the aerodynamic varaibles. The validation of this methodology has been made by comparison to expermient and simulation (LES) on two configurations of application. The first one is a weak reflected shock wave on a flat plate. The second one is the strong shock around an airfoil in a transonic regime. In both cases the incoming BL is laminar.Stability and resolvent analysis have been made. These approches have been able to caratirized the ocillator/noise amplifier behavior of the flow and to enabled a physical analysis of the unsteadinesses observed in the experiments.The case of the reflected shock wave is caracterized by three frequencies. The stability analysis shows that they don't correspond to globally unstable modes but to a noise amplifier behavior of the flow. The resolvent analysis identifies the three frequencies. The analysis of the optimal response, coupled with a local stability analysis, enables to proposed physical scenarii of these dynamics.In the case of the strong shock on an airfoil in transonic regime, the flow is globally unstable. Two unstable modes have been identified. The first one, at low frequency, correspond to the buffet phenomenon also observed in the turbulent case. The second one appears at higher frequency and correspond to the oscillation of the separation bubble formed at the feet of the shock.More generally, this thesis suggests that some dynamics of these two interactions result from the same mecanism linked to the breathing motion of the laminar separation bubble
Réchou, Anne. "Structure turbulente de la couche limite atmosphérique marine (expérience SOFIA)." Toulouse 3, 1995. http://www.theses.fr/1995TOU30058.
Tourigny, Pierre. "Inclusion de la condensation dans un modèle de couche limite." Thesis, McGill University, 1986. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=66104.
Rodier, Quentin. "Paramétrisation de la turbulence atmosphérique dans la couche limite stable." Thesis, Toulouse 3, 2017. http://www.theses.fr/2017TOU30343/document.
The modeling of the stable atmospheric boundary layer is one of the current challenge faced by weather and climate models. The stable boundary layer is a key for the prediction of fog, surface frost, temperature inversion, low-level jet and pollution peaks. Furthermore, polar regions, where stable boundary layer predominates, are one of the region with the largest temperature rise : the stable boundary layer modeling is crucial for the reduction of the spread of climate predictions. Since more than 15 years, the GABLS models intercomparison exercices have shown that turbulent mixing in the stable boundary layer is overestimated by numerical weather prediction models. Numerous models artificially strengthen the activity of their turbulence scheme to avoid a laminarization of the flow at a critical value of the gradient Richardson number. The existence of this threshold is only a theoretical and a numerical issues. Numerous observations and high-resolution numerical simulations do not support this concept and show two different regimes : the weakly stable boundary layer that is continuously and strongly turbulent; and the very stable boundary layer globally intermittent with a highly anisotropic and very weak turbulence. This thesis aims at improving the turbulence scheme within the atmospheric research model Méso-NH developped by Météo-France and the Laboratoire d'Aérologie, and the operational weather forecast model AROME. We use a traditional methodology based on the comparison of high-resolution simulations that dynamically resolve the most energetic turbulent eddies (Large-Eddy Simulations) to single-column simulations. Several LES covering the weakly and the very stable boundary layer were performed with Méso-NH. The limits of applicability of LES in stratified conditions are documented. The first part of the study deals with the overmixing in the weakly stable boundary layer. We propose a new diagnostic formulation for the mixing length which is a key parameter for turbulence schemes based on a prognostic equation for the turbulent kinetic energy. The new formulation adds a local vertical wind shear term to a non-local buoyancy-based mixing length currently used in Méso-NH and in the French operational model AROME. The new scheme is evaluated first in single-column simulations with Méso-NH and compared to LES, and then in the AROME model with respect to observations collected from the operational network of Météo-France. The second part presents a theoretical and numerical evaluation of a turbulence scheme based on two prognostic equations for the turbulent kinetic and potentiel energies. In stratified conditions, the heat flux contributes to the production of turbulent potential energy. The laminarization of the flow is then limited by a reduction of the destruction of the turbulent kinetic energy by a better representation of the anisotropy and a counter-gradient term in the heat flux. On the simulated cases, this new formulation behaves similarly than the scheme with one equation for the turbulent kinetic energy because the self-preservation mechanism is not dominant compared to the dissipation term. Further research should improve the turbulent kinetic energy dissipation closure in the very stable regime
Martel, Emmanuel de. "Simulation numérique des grandes échelles des interactions choc / couche limite." Paris 6, 2009. http://www.theses.fr/2009PA066285.
Estournel, Claude. "Etude de la phase nocturne de la couche limite atmospherique." Toulouse 3, 1988. http://www.theses.fr/1988TOU30042.
Brazier, Jean-Philippe. "Étude asymptotique des équations de couche limite en formulation déficitaire." Toulouse, ENSAE, 1990. http://www.theses.fr/1990ESAE0005.
Toussaint, Damien. "Couche limite turbulente sur paroi rugueuse : étude expérimentale et modélisation." Thesis, Toulouse, INPT, 2020. http://www.theses.fr/2020INPT0122.
Turbulent flows over rough walls can be found in various environmental and engineering situations. Focusing on aeronautical applications, unwanted rough surfaces are likely to decrease the overall efficiency of a system, skin friction, and heat transfer coefficients being generally increased compared to ideal smooth-wall situations. A careful account of the aerodynamic effects induced by surface roughness is therefore important in a design process, and several prediction strategies may be considered. The Discrete Element Roughness Method (DERM) is considered in the present study. This approach aims at resolving the averaged roughness effects and is derived by ensemble- and volume-averaging the Navier–Stokes equations, yielding three unknown terms in the momentum equation: the Reynolds stress and dispersive stress tensors and the average drag force acting on the roughness elements. The present work aims at proposing guidance for their modelling. First, a LDV measurement campaign was conducted to investigate turbulent boundary layer flows over rough surfaces. Measurements were especially performed within the roughness wake regions, that are not extensively investigated in the literature. Second, RANS simulations of turbulent channel flows over resolved rough surfaces were performed. The numerical results were then compared to the experimental data to assess the validity of the RANS simulations. Finally, these numerical results were analysed to highlight the behavior of the specific DERM terms and propose guidance for their modeling
Tanière, Anne. "Comportement de particules solides au sein d'une couche limite turbulente." Valenciennes, 1996. https://ged.uphf.fr/nuxeo/site/esupversions/cbb40afa-4540-4418-9ba5-d75c8e0e8fcd.
Estournel, Claude. "Etude de la phase nocturne de la couche limite atmosphérique." Grenoble 2 : ANRT, 1988. http://catalogue.bnf.fr/ark:/12148/cb376133949.
Bayeux, Charlotte. "Méthode intégrale pour la couche limite tridimensionnelle - Applications au givrage." Thesis, Toulouse, ISAE, 2017. http://www.theses.fr/2017ESAE0047/document.
Icing has since long been identified as a serious issue in the aeronautical world. Ice accretion occurs whensupercooled water droplets impinge on a surface, particularly the leading edge of a wing or an engine inlet, andfreeze after the impingement. This can lead to degradation of aerodynamic performances, sensor malfunctionor engine damage. This is why this issue is being carefully studied. The lengthy and costly flight and windtunnel tests have made numerical simulation of ice accretion a necessary tool in the aircraft design andcertification process. The present work deals with the 3D numerical modeling of ice accretion, and more particularly the modeling of the dynamic and thermal boundary layers that develop around an iced body. Since numerical tools must befast and robust, the approach proposed in this thesis for aerodynamic computation is a coupled Euler/integralboundary layer method. Thus, an integral model is developed to represent the development of the dynamicboundary layer. The thermal part is modeled either by a simplified method based on algebraic approaches,or by an integral method. This modeling of the dynamic and thermal boundary layers is valid on smoothor rough walls and provides the friction coefficient and heat exchange coefficient that are necessary for thecalculation of ice accretion. The integral boundary layer equations, associated with their closure relations,are then solved by a Finite-Volume method on unstructured surface mesh, that is well suited for complexgeometries. In addition, specific numerical treatments are implemented to improve the accuracy of the methodin the vicinity of the stagnation point and to make the code robust to separated boundary layers.After validation of the boundary layer method, the code is used in ONERA’s 2D and 3D icing tools foricing applications. This demonstrates the value of the method in terms of robustness and accuracy comparedto the boundary layer codes more commonly used in current icing tools
Lagrée, Pierre-Yves. "Structures interactives fluide parfait/couche limite en hypersonique, variations sur le theme de la triple couche." Paris 6, 1992. http://www.theses.fr/1992PA066207.
Salinas, Hervé. "Stabilité linéaire et faiblement non linéaire d'une couche limite laminaire compressible tridimensionnelle par l'approche PSE." Toulouse, ENSAE, 1998. http://www.theses.fr/1998ESAE0024.
Vartanian, Christian. "Développement de méthodes expérimentales permettant de relier la structure spatio-temporelle de l'écoulement au champ de pression pariétale." Poitiers, 2003. http://www.theses.fr/2003POIT2279.
The aim of this work is to determine methods witch allow us to understand the link between the flow spatio-temporal stucture and the wall pressure field tanks to simultaneous experimental velocity and pressure data. A new ewperimental setup has been carried out in order to generate at demand two contra-rotative vortex, and this generation is reproductible. The simultaneous study of the velocity and wall pressure field was done in pariculary by particule imagery velocimetry and wall pressure transducers. The vortex influence during is evolution is caracterised on the turbulent boundary layer and in term of wall pressure signature. An automotive application of these detection and identification methods of structure and wall pressure fluctuation is done
Zegadi, Rabah. "Contribution à l'étude de la couche de surface atmosphérique, en situation stable, simulée en soufflerie." Ecully, Ecole centrale de Lyon, 1991. http://www.theses.fr/1991ECDLA012.
Isdiyana. "Simulation lagrangienne du transport, de particules solides en suspension dans une couche limite turbulente." Ecully, Ecole centrale de Lyon, 1993. http://www.theses.fr/1993ECDL0039.
Augier, Eric. "Etude de la modification d'une couche limite turbulente par l'insertion d'un manipulateur type réducteur de trainée." Ecully, Ecole centrale de Lyon, 1992. http://www.theses.fr/1992ECDL0011.
Cheinet, Sylvain. "La paramétrisation des couches limites convectives claires et nuageuses." Palaiseau, Ecole polytechnique, 2002. http://www.theses.fr/2002EPXX0024.
De, Souza Carlos Augusto. "Techniques de maillage adaptatif pour le calcul des solutions de coques élastiques minces." Paris 6, 2003. http://www.theses.fr/2003PA066489.
MAQUEVILLE, BENOIT DE. "Application de methodes integrales au calcul de la couche limite du deuxieme ordre et au calcul de la couche limite sur des maillages non structures." Paris 6, 1995. http://www.theses.fr/1995PA066385.
Schwartz, Heidi. "Instrumentation et mesures ultrasonores dans un écoulement d'air en couche limite : application à la détermination de l'angle d'incidence d'un aéronef." Thesis, Tours, 2014. http://www.theses.fr/2014TOUR4012.
In the field of aeronautics, the angle of attack of an aircraft is an essential flight parameter. The aim of this work is to analyze the systems based on measurements using ultrasonic times of flight, and to realize an aeronautic ultrasonic system. The probe that has been developed during this work is made of ultrasonic transducers, transmitters and receivers of ultrasonic waves. Measuring delays between these waves may allow the determination of the angle of attack, thanks to an analytical calculation. Limits of this formula are studied during this work because it may only be used in uniform fields. First of all, a numerical model based on the ray theory is developed to take into account the propagation effect of a turbulent boundary layer. Afterwards, experiments are conducted in an anechoic wind tunnel. The experimental delays obtained are similar to those calculated with the developed code. Furthermore, comparison between experimental delays and those calculated thanks te basic expressions of times of flight, shows similar results particularly at high angles. Finally, the angles of attack are determined thanks to measurements of ratio between experimental delays. The angle is deducted thanks to two different tools, a numerical abacus based on the developed code, and an analytical abacus. The results show that the analytical abacus is the most appropriate tool for determination of angles of attack. Indeed, the boundary layer part becomes negligible when ratio between delays is taken into account. The approximation of the code concerning the choice of the shots of rays used for the calculation may be the main source of errors
Andoh, Honoré Yobouet. "Refroidissement de paroi par effusion : Etude expérimentale." Lyon, INSA, 1992. http://www.theses.fr/1992ISAL0088.
One solution for the cooling of combustion chamber walls, when they are porous, consists of cooling them by effusion of a cold gas flowing from outside to inside this work aims to analyse the performance of such a system. A model of flowing throw the wall, based on a Blasius type law and solved by a finite difference method, was developed. Compared to various model found in the literature, it was applied to experiments with various fluids, operating temperatures and pressures. The model of beat transfer inside the wall uses the energy equation and a finite difference method solving. It is allows to study the sensitivity of mechanism to various parameters. One at them - the internal convective heat transfer coefficient is preponderant. Its value is obtained by semi-empirical equation given by the literature or by an indirect experimental method, difficult to carry out due to the great thermal involved. A simple modelling of the boundary layer, using the assumption of a laminar layer moving perpendicular to the wall, allows to calculate the heat flux get by the wall. A boundary layer of a few hundredth millimetres thickness is enough to considerably limit the flux. A global simulation program is used to analyse the performance of the studied cooling mode. When the main parameters vary, pressures, up-stream and down-stream to the wall, cold and hot gases temperatures, material, fluid, internal convection coefficient, boundary layer thickness
Forte, Maxime. "Contrôle d'écoulement par actionneur plasma de type décharge à barrière diélectrique : application à l'amélioration de la pulvérisation dans les injecteurs de turboréacteurs." Poitiers, 2007. http://www.theses.fr/2007POIT2339.
Recently, jet engine manufacturers have pointed out some difficulties in spraying fuel correctly inside combustion chambers for some critical regimes (such as starting or refiring). The principles used in current air-assisted injectors are no longer efficient when airflow velocities are low (<30 m/s). Plasma actuators have been thought to modify the airflow around the injectors in order to improve spraying as they can induce an airflow called “ionic wind” inside the boundary layer. The first part of this study was about the observation and the optimization of the DBD plasma actuator. A parametric study was performed in order to increase the velocity of the airflow induced by such actuators. The results from the velocity measurements (Pitot probe, LDV) show that an optimization of geometrical and electrical parameters enables the generation of ionic wind up to 8 m/s at 0. 5 mm from the wall. The second part of the study was more applicable to industrial usage. An injector model has been built and fitted with an optimized DBD actuator. PIV and LDV velocity measurements were performed to show the effect of the actuation on the airflow around the injector for upstream velocities in the range of 5 to 30 m/s. Additional spectral analyses performed with recent slotting technique have shown that the actuator is able to generate coherent structures in the wake of the injector, with an adjustable frequency
Dumouchel, Christophe. "Problèmes liés à la conception d'un pulvérisateur mécanique : hydrodynamique de chambre et instabilité de nappe." Rouen, 1989. http://www.theses.fr/1989ROUES042.
Randriamampianina, A. Arthur. "Contrôle d'une couche limite laminaire et turbulente : influence de l'aspiration sur le bruit de champ proche et loitain dans une couche limite autour d'un corps bidimensionnel." Aix-Marseille 1, 1988. http://www.theses.fr/1988AIX11149.
Randriamampianina, A. Arthur. "Contrôle d'une couche limite laminaire et turbulente influence de l'aspiration sur le bruit de champ proche et lointain dans une couche limite autour d'un corps bidimensionnel /." Grenoble 2 : ANRT, 1988. http://catalogue.bnf.fr/ark:/12148/cb376178892.
Menut, Laurent. "ETUDE EXPERIMENTALE ET THEORIQUE DE LA COUCHE LIMITE ATMOSPHERIQUE ENAGGLOMERATION PARISIENNE." Phd thesis, Université Pierre et Marie Curie - Paris VI, 1997. http://tel.archives-ouvertes.fr/tel-00116659.
l'atmosphère libre. C'est la partie inférieure de l'atmosphère qui est
sous l'influence directe des processus terrestres. Son extension verticale va de
la surface à quelques centaines de mètres d'altitude et
dépend directement de tous les paramêtres météorologiques (vent,
température, humidité, insolation), mais aussi de la topographie et du type
d'environnement (océan, continental rural ou urbain). L'amplitude de cette
extension va guider la dispersion des aérosols, notamment en milieu urbain
dans le cas des polluants atmosphériques.
L'accroissement de plus en plus important de la pollution est devenu aujourd'hui
un des principaux problèmes de la vie en milieu urbain. Son origine est
anthropique (circulation automobile, usines...) et à défaut de pouvoir
éliminer rapidement sa cause, il semble indispensable de bien comprendre les
phénomènes qui conduisent à son accumulation excessive afin d'essayer d'en
controler les effets. Cette compréhension ne pourra se faire que par une
étude précise de la couche limite urbaine.
Dans le cadre de cette étude, notre attention s'est portée sur la CLA
urbaine en région Parisienne. Ce milieu a jusqu'à présent peu fait l'objet
d'études, ce qui a conduit à la mise en place de la première campagne de
mesures : la campagne ECLAP, fruit d'une collaboration entre le CNRS et EDF,
pour la caractérisation des processus dynamique et thermique, par
l'expérimentation et la simulation numérique.
Nakano, Tamon. "Étude numérique de l’interaction choc/couche limite en géométrie de révolution." Thesis, Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique, 2018. http://www.theses.fr/2018ESMA0013/document.
Shock wave/boundary layer interactions (SWBLI) are present in various aerospace engineering applications.They can be associated with separated regions yielding low-frequency unsteadiness, which have mainly been studied in planar geometries. The present study aims at characterizing this type of interaction in a cylindrical configuration. A direct numerical simulation solver has been developed and validated with various test cases. It is based on a high-order finite difference based hybrid schemes (6th order centered scheme/5thorder WENO), extended to curvilinear geometries. Transverse curvature effects on properties of spatially developing supersonic boundary layer at Mach 3 are first examined. It is shown that the increase of the relative curvature of the boundary layer tends to reduce the fluctuation energy at lower frequencies near the wall, while reinforcing the perturbations at higher frequencies in the upper zone of the boundary layer.In comparison with the planar case, the transverse curvature leads to a significant re-organization of the boundary layer structures and a subsequent modified behavior of the invariants of anisotropy turbulent stress tensor. It however only leads to slightly modified distributions of Reynolds stress and a rather similar overall balance of turbulent kinetic energy through the boundary layer. The second part of this study is dedicated to the unsteady motions of the shock/separation zone in a cylinder/compression flare configuration for which the full cylindrical geometry is taken into account. The shock distortions in the azimutal direction appears to be mainly associated to the organization of the upstream vortex structures and the subsequent azimutal fluctuations of the separation line. It is shown that the energy of the fluctuating wall pressure is more amplified for higher order azimutal modes. The contributions to lateral forces, associated to the first mode, are dominated by low-frequencies only upstream of the separation line in the intermittent region. They become more dominant in the middle frequency range downstream of the reattachment zone on the ramp. It is also shown that the low-frequency activity at the wall is progressively due to higher order azimuthal modes through the interaction zone