Добірка наукової літератури з теми "Performances aérodynamiques"
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Статті в журналах з теми "Performances aérodynamiques"
Bekhti, Ahmed, and Ouahiba Guerri. "Influence de la rugosité sur les caractéristiques aérodynamiques d’un profil de pale d'éolienne." Journal of Renewable Energies 15, no. 2 (October 23, 2023): 235–47. http://dx.doi.org/10.54966/jreen.v15i2.315.
Повний текст джерелаSimon, Jacques. "Methode d'essai aérodynamique et analyse des paramètres géometriques modifiant les performances des exutoires." Journal of Wind Engineering and Industrial Aerodynamics 45, no. 3 (July 1993): 325–38. http://dx.doi.org/10.1016/0167-6105(93)90103-u.
Повний текст джерелаRezig, Ahmida, Ahmed Yousfi, Sylvain Fréour, and Frédéric Jacquemin. "Effet de l’érosion par des particules de sable sur la performance des pales d’éoliennes dans les zones arides et semi-arides." MATEC Web of Conferences 261 (2019): 05001. http://dx.doi.org/10.1051/matecconf/201926105001.
Повний текст джерелаRezig, Ahmida, Ahmed Yousfi, Sylvain Fréour, Frédéric Jacquemin, and Samuel Branchu. "Nouvelle méthode de maintenance CBM pour améliorer la durée de vie des pales d’éoliennes implantées dans les zones arides." MATEC Web of Conferences 261 (2019): 01001. http://dx.doi.org/10.1051/matecconf/201926101001.
Повний текст джерелаNouioua, Ali, and Rabah Dizene. "Modélisation d’un écoulement pulsatif et oscillatoire autour d’une pale d’éolienne HAWT Application au décrochage dynamique." Journal of Renewable Energies 18, no. 1 (October 18, 2023). http://dx.doi.org/10.54966/jreen.v18i1.483.
Повний текст джерелаZergane, Slimane, and Arezki Smaïli. "Optimisation de la micro-localisation des aérogénérateurs dans un parc éolien." Journal of Renewable Energies 14, no. 4 (October 24, 2023). http://dx.doi.org/10.54966/jreen.v14i4.295.
Повний текст джерела"Extended summary of “Methode d'essai aérodynamique et analyse des paramètres géometriques modifiant les performances des exutoires” (Smoke ventilators: an approach for the determination of their performances and some results) by Jacques Simon." Journal of Wind Engineering and Industrial Aerodynamics 45, no. 3 (July 1993): 339. http://dx.doi.org/10.1016/0167-6105(93)90104-v.
Повний текст джерелаДисертації з теми "Performances aérodynamiques"
Dumont, Antoine. "Calculs de gradients pour l'optimisation des performances aérodynamiques d'un rotor d'hélicoptère en vol stationnaire." Poitiers, 2010. http://www.theses.fr/2010POIT2327.
Повний текст джерелаThis thesis work is dedicated to the development of efficient sensitivity analysis methods in the context of aerodynamic shape optimization considering the application of an isolated helicopter rotor in hover, for which the flow can be considered as steady in a rotating frame. Sensitivity quantities represent in fact an important information to any gradient based method used to solve local optimisation problems. For the flow analysis, the governing equations (RANS) are discretized using a finite volume method and are solved with the ONERA CFD code elsA. The two methods implemented in elsA for the specific formulation in a rotating frame are the discrete direct differentiation method and the discrete adjoint method which presents the interesting characteristic of being quasi-independent in terms of computational cost with respect to the number of shape parameters of the problem. They both rely on the differentiation of the flow solver and of the cost function which, in that context, is the aerodynamic efficiency of a hovering rotor, named the figure of merit (FM). Some single-objective shape optimizations have been done with the goal of improving the maximum of figure of merit of a rotor. They show the capability of the optimization process to converge to blade planform that improve significantly the figure of merit over a large range of thrust and that give an increase in load capacity of the rotor. This work could be used to perform local optimization of any rotary wing or fan in purely axial flight condition
Schneider, Alexandra Patrizia. "Aerodynamic and aeroelastic investigation of a composite fan for ultra-high-bypass-ratio aircraft engines." Electronic Thesis or Diss., Ecully, Ecole centrale de Lyon, 2024. http://www.theses.fr/2024ECDL0018.
Повний текст джерелаModern low-speed Ultra-High Bypass Ratio (UHBR) fans operate predominantly on the flat part of the compression characteristic, have shorter intake lengths, and employ flexible, lightweight, composite blades. These changes promote the evolution of different types of instabilities with multi-physical interactions such as convective non-synchronous vibration (NSV). To enable further technological ad-vancements, experimental benchmark data on representative geometries required. Within this con-text, the European project CATANA was initiated at Ecole Centrale de Lyon. The open-test-case fan stage ECL5 was designed, following industrial guidelines, and tested experimentally on the facility ECL-B3. This thesis presents the experimental results of the CATANA project. The experimental investiga-tion of the ECL5 reference configuration shows that all design goals have been reached. The machine is operational in a wide range and aerodynamic performance at design condition is exactly coincident with the numerical prediction. In contrast, instability mechanisms are more complex than predicted by the employed numerical methods. Through application of synchronized multi-physical instrumenta-tion, the involved complex fluid-structure interaction is resolved. The analysis of the influence of in-flow conditions and geometrical and structural system symmetry allows to identify the sensitivity of aerodynamic and structural characteristics and the behavior close to the stability limit. The investiga-tion of a second rotor configuration featuring structural mistuning highlights the importance of geo-metrical blade-to-blade variations. They cause an asymmetry of the aerodynamic field at the blade tip and suppress coherently propagating aerodynamic disturbances resulting in a delayed onset of NSV. The results presented in this thesis provide a comprehensive multi-physical characterization of the ECL5 fan stage and serve as a benchmark data set for the validation of numerical simula-tions
Belleil, Cédric. "Calcul direct des performances aérodynamique et acoustique d'un silencieux industriel par modélisation CFD, et optimisation aérodynamique." Mémoire, École de technologie supérieure, 2005. http://espace.etsmtl.ca/338/1/BELLEIL_C%C3%A9dric.pdf.
Повний текст джерелаLv, Peng. "Performance aérodynamique et structurelle du rotor flexible pour micro-drones." Thesis, Toulouse, ISAE, 2014. http://www.theses.fr/2014ESAE0058/document.
Повний текст джерелаThe wind tunnel tests were conducted to explore the performance difference caused by the potential twist deformation between baseline blades and flexible blades. The balance was built in SaBre wind tunnel for measuring the thrust and torque of blades. The BEMT predictions of blades with varied twist were also performed in hover and forward flight, respectively. In hover,flexible blades cannot help in improving the FM at light disk loading since the twist generated on flexible blades is probably beyond the ideal hover twist. In forward flight, the propulsive efficiency η of flexible blades is mostly higher than baseline blades due to the beneficial twist generated in rotation. A Particle Image Velocimetry (PIV) approach of loads determination was developed based on control volume method to obtain thrust and torque of small-scale proprotor,especially for off-optimum conditions. The pressure Poisson equation was implemented for the pressure estimation based on the PIV velocity data. The axial velocity of flexible blades is found to be lower than baseline blades on the same station at downstream. This corresponds to the lower inflow ratio distribution along flexible blade, which results from the negative twist deformation. For both baseline blades and flexible blades, the thrust differences between PIV test 2 and balance are larger when compared to the differences between PIV test 1 based on nearfield and balance. The Laser Displacement Sensor (LDS) technique was employed for measuring the stationary deformation of rotating flexible blades. By obtaining the LDS point cloud, the bending and torsion of the rotating blade were identified using the multiple regressions
Chabroux, Vincent. "Approche aérodynamique et biomécanique de l'amélioration des performances de cyclistes en course contre la montre." Thesis, Aix-Marseille 2, 2010. http://www.theses.fr/2010AIX22037/document.
Повний текст джерелаThe aim of this study is to determine the aerodynamic and biomechanical factors influencing cyclists performance during Time Trial stage (TT). The aerodynamic drag force represents over 90% of the power generated by the cyclist during TT stage. The aerodynamic optimization of the cyclist posture and equipment is thus a main objective. Experimentations were carried out in the wind tunnel S1L of the Institute of Movement sciences, in order to measure the aerodynamic drag force of cyclist according to different configurations. Measurements of the projected frontal led to a modeling of the cyclist frontal area value according to postural parameters. Aerodynamic performance of several TT helmets was characterized by measurement of the velocity fields in their downstream wake using a PIV-3C method (Particle Image Velocimetry 3 components). Results of this study have identified an optimized geometry of TT helmets. The aim of the biomechanical approach is to study the influence of the aerodynamic postural parameters studied on the performance of the cyclists. An inverse dynamics models is used to determine the torques and forces at each leg joint according to the saddle position and the power developed. The inverse dynamic calculation requires measurement of the pedal forces and the cycling motion. The motion analysis system VICON was used and two special 6 components sensors were design for this application. Results of this study have identified postural parameters increasing the performance. The synthesis of the factors influencing aerodynamic and biomechanical performances achieves a performance improvement of about 3%
Ortolan, Aurélie. "Etude aérodynamique de ventilateurs axiaux réversibles à performance duale compresseur/turbine élevée." Thesis, Toulouse, ISAE, 2017. http://www.theses.fr/2017ESAE0019/document.
Повний текст джерелаIn the more electric aircrafts context, the in-flight windmilling operation of conventional onboard axial fans is regarded as a functioning mode that enables energy recovery. Poor turbine efficiencies of classical geometries, due to massive separations, require to design a reversible machine. The latter allows a dual compressor/turbine functioning with high performances in both modes to capitalize the equipment throughout the mission. In this study, the relevance of psi-phi formalism to multi-quadrant approach is underlined. The flow analysis from compressor to load-controlled windmill enables to highlight generic properties of windmilling flows as well as dual machines specificities. The flow mechanisms and geometrical parameters impacting the performances along the operating line are also identified. Finally, an optimized dual machine design is proposed
Toubin, Hélène. "Prediction and phenomenological breakdown of drag for unsteady flows." Thesis, Paris 6, 2015. http://www.theses.fr/2015PA066576/document.
Повний текст джерелаAccurate drag prediction is now of a major issue for aircraft designers. Its phenomenological sources need to be identified and quantified for an efficient design process. Far-field methods, which allow such phenomenological drag breakdown, are however restricted to steady flows. This study consists in developing a far-field drag prediction method aiming at a phenomenological breakdown of drag for unsteady flows. The first step has consisted in generalizing the steady formulation of Van der Vooren to unsteady flows, starting from a new rigorous proof. Axes for the improvement of the robustness and physical background have then been explored. Acoustic contributions have in particular been highlighted and quantified. The resulting five-components formulation has then been applied to simple cases, in order to validate as best as possible the phenomenological breakdown. The behavior of the drag components has proved to be consistent with the physics of the flow. Finally, the method has been applied to complex cases in order to demonstrate its capabilities: a 3-D case and a flow simulated by the ZDES method. In the future, it would be interesting to further improve the definition of the induced drag component, for example by using velocity-based formulations. As far as the application cases are concerned, the performance evaluation of a Counter-Rotating-Open-Rotor would strongly benefit from such a method. Unsteady optimization of one of the drag component could also be contemplated. Finally, applications in aeroelasticity or flapping flight would be an interesting perspective
Laverne, Thomas. "Aérodynamique des éoliennes à axe horizontal : effets de la turbulence de l'écoulement amont et de la rotation sur le comportement aérodynamique des profils constitutifs : conséquences sur le fonctionnement et les performances." Orléans, 2003. http://www.theses.fr/2003ORLE2053.
Повний текст джерелаLauriau, Pierre-Thomas. "Caractérisation de la performance aérodynamique d'un étage de turbine radiale à géométrie variable, en fonctionnement hors-adaptation." Thesis, Toulouse, ISAE, 2019. http://www.theses.fr/2019ESAE0004/document.
Повний текст джерелаThe technological mutation of transport in general and aeronautics in particular, engaged to the European level, leads to an evolution of more economical and fuel-efficient aircrafts. It strongly impacts the environmental control systems by a partial electrification which does not need an air bleeding on the engine anymore. Then it is necessary to insure a large output range through the turbine, element of the turbomachine which forms the heart of the air conditioning « pack », while providing the maximum amount of possible power on the whole range. The classical turbine stage cannot insure the specified output range. Then it is replaced by a variable geometry radial inflow turbine. This turbine stage has to function from the maintenance phase on the ground (weak output, strong expansion ratio) to the en route phase (strong output, weak expansion ratio). It also has to guarantee its role during the others phases of flight and in case of multiple failures power. So the problematic is to design a turbine such that its geometry varies in operation and adapt itself to the changing operating with the best possible efficiency on the widest possible range. Thus it is primordial to understand beforehand the complexity of flows for this kind of geometry, and how the variable geometry device affects the flow topology in the turbine stage. In particular, the presence of clearances in the static parts of the stage creates a vortex perturbation upstream from the rotor. The impact of this perturbation on the main flow, its interaction with secondary flows, must be detailed. The influence of the perturbation localisation, its intensity, must be analysed, in the complex variable geometry context. The understanding of phenomenon involved and responsible for the downgrade of performance in the turbine stage, will allow defining a specific strategy of design. The improvement of performance for the turbine will enable to restrict the required power on the electrical engine for limiting the on board weight, and then the fuel consumption. The selected methodology to broach this problematic, is divided into four parts. Firstly, a bibliographic part in order to appropriate physics phenomenon related to the flow in a variable geometry turbine will be conducted, together with a state of art about the different existing technological solutions. Secondly, some numerical simulations will be set to propose a methodology of robust calculations for performance prediction and, to discriminate different design options. The third step consists in an experimental phase representing the main work of the thesis. It will consist in the definition of a specific module instrumented for tests representative of the turbine on aircraft functioning. It will provide a database for analysing the flow and validating the numerical simulations, and to quantify the effects of integration. These numerical and experimental studies will be led jointly, such that the general analysis takes advantage of complementarity of both approaches. The last step of this study aims at conditioning the results achieved and the know-how for industrial application
Noubel, Hugo. "Etude expérimentale du comportement aérodynamique et optimisation des performances des planeurs hypersoniques dans des écoulements supersoniques et hypersoniques raréfiés." Electronic Thesis or Diss., Orléans, 2024. http://www.theses.fr/2024ORLE1001.
Повний текст джерелаThe main objective of this thesis work is to experimentally characterize the impact of viscous effects on the aerodynamic performance of hypersonic gliders. The study includes six low-pressure flows (ranging from 0.068 Pa to 71.11 Pa) from the MARHy wind tunnel, four supersonic flows (Mach 2 and Mach 4), and two hypersonic flows (Mach 20). A total of 6 models were tested, aiming to study geometries with different degrees of optimization and to understand the impact of viscous effects one ach of them. Various diagnostics were used to carry out this study : Firstly, an aerodynamic balance was developed to measure the drag and lift forces of the different configurations. Next, shock waves were visualized using glow discharge imaging. Finally, a parietal pressure study was carried out on two hypersonic gliders. This thesis work establishes a broad experimental database on hypersonic gliders in the rarefied regime. Force studies have enabled us to quantify the evolution of glide ratio during atmospheric re-entry as a function of the degree of rarefaction (Tsien parameter). As far as angles of attack are concerned, formulations taking viscous effects into account have been established and can be used in the optimization of high-altitude waveriders. A hypersonic glider incorporating these data has been tested and shows promise at high altitude. Throughout this thesis, results have highlighted the impact of viscous effects on the aerodynamic performance of hypersonic gliders
Книги з теми "Performances aérodynamiques"
Symposium, North Atlantic Treaty Organization Advisory Group for Aerospace Research and Development Fluid Dynamics Panel. Aerodynamic engine/airframe integration for high performance aircraft and missiles =: L'intégration aérodynamique des moteurs et des cellules dans les avions et les missiles à hautes performances. Paris: AGARD, 1992.
Знайти повний текст джерелаAircraft Performance. VDM Verlag, 2009.
Знайти повний текст джерелаAircraft Performance: An Engineering Approach. Taylor & Francis Group, 2017.
Знайти повний текст джерелаStengel, Robert F. Flight Dynamics: Second Edition. Princeton University Press, 2022.
Знайти повний текст джерелаStengel, Robert F. Flight Dynamics. Princeton University Press, 2015.
Знайти повний текст джерелаStengel, Robert F. Flight Dynamics. Princeton University Press, 2015.
Знайти повний текст джерелаFlight Dynamics: Second Edition. Princeton University Press, 2022.
Знайти повний текст джерелаFlight Dynamics. Princeton University Press, 2004.
Знайти повний текст джерелаТези доповідей конференцій з теми "Performances aérodynamiques"
Schreiber, Johannes, Xavier Ottavy, Ghislaine Ngo Boum, Stéphane Aubert, and Frédéric Sicot. "Numerical Simulation of the Flow Field in a High Speed Multistage Compressor: Study of the Time Discretization Sensitivity." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-42114.
Повний текст джерела