The design of supersonic flow paths for scramjet engines and high Mach number shock tunnel nozzles is complicated by high temperature flow effects and multidimensional inviscid/ viscous flow interactions. Due to these complications, design in the past has been enabled by making flow modelling simplifications that detract from the accuracy of the flow analysis. A relatively new approach to designing aerodynamic bodies, which automates design and does not require as many simplifying assumptions to be effective, is the coupling of a computational flow solver to an optimization algorithm. In this study, a new three-dimensional space-marching computational flow solver is developed and coupled to a gradient-search optimization algorithm. This new design tool is then used for the design optimization of an axisymmetric scramjet flow path and two high Mach number shock tunnel nozzles. The flow solver used in the design tool is an explicit, upwind, space-marching, finite-volume solver for integrating the three-dimensional parabolized Navier-Stokes equations. It is developed with an emphasis on simplicity and efficiency. Cross-stream fluxes are calculated using Toro's efficient upwind, linearized, approximate Riemann solver in flow regions of slowly varying data, and an Osher type solver in the remainder of the flow. Vigneron's technique of splitting the streamwise pressure gradient in subsonic regions is used to stabilise the flux calculations. A three-dimensional implementation of an algebraic turbulence model, a finite-rate chemistry model and a thermodynamic equilibrium model are also implemented within the solver. A range of test cases is performed to (1) validate and verify the phenomenological models implemented within the solver, thereby ensuring the simulation results used for design are credible, and (2) demonstrate the speed of the solver. The first application of the new computational design tool is the design of a scramjet flow path, which is optimized for maximum axial thrust at a flight Mach number of 12. The optimization of a scramjet flow path has been examined previously, however, this study differs to others published in that the flow is modelled using a turbulence model and a finite-rate chemical reaction model which add to the fidelity of the simulations. The external shape of the scramjet vehicle is constrained early on in the design process, therefore, the design of the scramjet is restricted to the internal flow path. Because of this constraint, and the large internal surface area of the combustor and the high skin friction iv within the combustor, the net calculated force exerted on the scramjet for both the initial and optimized design is a drag force. The drag force of the initial design, however, is reduced by 60% through optimization. The second application of the design tool is the wall contour of an axisymmetric Mach 7 shock tunnel nozzle, which is computationally optimized for minimum test core flow variation to a level of +/- 0.019 degrees for the flow angularity and +/- 0.26% for the Pitot pressure. The design is verified by constructing a nozzle with the optimized wall contour and conducting experimental Pitot surveys of the nozzle exit flow. The measured standard deviation in core flow Pitot pressure is 1.6%. However, because there is a large amount of experimental noise, it is expected that the actual core flow uniformity may be better than indicated by the raw experimental data. The last application of the computational design tool is a contoured Mach 7 square cross-section shock tunnel nozzle. This is a three-dimensional optimization problem that demonstrates the versatility of the design tool, since the effort required to implement the optimization algorithm is independent of the complexity of the flow-field and flow solver. Optimization results show that the variation in the test core flow properties could only be reduced to a Mach number variation of +/- 7% and flow angle variation of +/- 1.2 degrees ,for a short nozzle suitable for a shock tunnel. The magnitudes of the optimized nozzle exit flow deviations for the short nozzle and two other longer nozzles indicate that generating uniform flow becomes increasingly difficult as the length of square cross-section nozzles is reduced. Overall, the current research shows that coupling a flow solver to an optimization algorithm is an effective and insightful way of designing scramjets and shock tunnel nozzles.

Αντικείμενο της παρούσας διδακτορικής διατριβής αποτέλεσε η ανάπτυξη μιας ακριβούς υπολογιστικής μεθοδολογίας για τη μελέτη της μαγνητοϋδροδυναμικής και θερμικής ροής ενός ηλεκτρικώς αγώγιμου ρευστού υπό την επίδραση ενός εξωτερικού μαγνητικού πεδίου, για μεγάλο φάσμα τιμών των παραμέτρων της ροής. Η μελέτη της διαμόρφωσης της μαγνητορευστοδυναμικής και θερμικής ροής των ηλεκτρικώς αγώγιμων ρευστών, όπως είναι τα υγρά μέταλλα, υπό την επίδραση της εφαρμογής ενός εξωτερικού μαγνητικού πεδίου, είναι ιδιαίτερα σημαντική για την εκτίμηση της μείωσης της αξονικής βαθμίδας της πίεσης, του συντελεστή μεταφοράς θερμότητας και άλλων φυσικών ποσοτήτων, σε μια σειρά προβλημάτων όπως είναι η σταθεροποίηση και ο περιορισμός του πλάσματος, η ψύξη των αντιδραστήρων σύντηξης με υγρά μέταλλα, η χύτευση μετάλλων με ηλεκτρομαγνητικά μέσα, η χρήση ηλεκτρομαγνητικών αντλιών για υγρά μέταλλα, στη γεωλογία, για τη μελέτη του εσωτερικού της Γης, και στην αστροφυσική όπου μελετώνται μεταξύ άλλων αστέρες, νεφελώματα και σχετικιστικά τζετ. Η ροή θεωρείται ασυμπίεστη και στρωτή, ενώ μελετάται για τις περιπτώσεις της πλήρως ανεπτυγμένης και της αναπτυσσόμενης ροή στην περιοχή μεταξύ δύο ομοαξονικών ευθύγραμμων ή καμπύλων αγωγών κυκλικής διατομής, υπό την επίδραση ισχυρού εξωτερικού μαγνητικού πεδίου. Τα τοιχώματα των αγωγών είναι ηλεκτρικώς μονωμένα και ανάλογα με το πρόβλημα βρίσκονται σε διαφορετικές σταθερές θερμοκρασίες ή σε διαφορετικές ροές θερμότητας. Από τα αποτελέσματα προέκυψε πως το μαγνητικό πεδίο έχει πολύ σημαντική επίδραση στην κατανομή της ταχύτητας και στην πτώση πίεσης, ενώ η επίδραση του στη μετάδοση θερμότητας στην περίπτωση των υγρών μετάλλων είναι μηδαμινή. / The aim of the present doctorate thesis was the development of an accurate και robust computational methodology for the study of the magnetohydrodynamic flow of an electrically conducting fluid under the effect of an external magnetic field, for large regions of values of the parameters of the flow. The study of the magnetohydrodynamic και thermal flow of an electrically conducting fluid, such as liquid metals, is very important for the estimation of the pressure drop, the heat transfer coefficient και other physical quantities in several engineering applications such as stabilization και control of plasma, fusion reactor blankets, metallurgy, electromagnetic pumps, geology for the study of the inner core of the earth και astrophysics where stars, nebula και relativity jets are studied. The flow is considered as incompressible και laminar και it is studied for the cases of the fully developed και the developing flow in the region between two homoaxial straight or curved ducts of circular cross-sections, under the effect of an external magnetic field. The duct walls are considered as electrically insulated και maintained at uniform temperatures or uniform heat fluxes. The results show that the magnetic field has a significant effect on the velocity distribution και the pressure drop και a minor effect on the heat transfer.

Orientador: José Roberto Nunhez / Dissertação (mestrado) - Universidade Estadual de Campinas, Faculdade de Engenharia Química / Made available in DSpace on 2018-08-17T07:13:04Z (GMT). No. of bitstreams: 1 Olino_AnaLeticiaMonteiro_M.pdf: 2635476 bytes, checksum: 1044b4e4ad54faed575660cb81c06763 (MD5) Previous issue date: 2010 / Resumo: Um impelidor ideal para suspensões deve prover a suspensão completa ou homogeneização utilizando o mínimo de energia. O fluxo em um tanque agitado depende da geometria do impelidor, do diâmetro e da localização deste, do diâmetro e do fundo do tanque e da geometria de internos. A Fluidodinâmica Computacional (CFD) é uma ferramenta poderosa para predizer fluxos tridimensionais e distribuição de concentração de sólidos produzidos por impelidores de qualquer configuração geométrica. Este estudo pretende aumentar a capacidade de bombeamento de um impelidor de bombeamento axial, chamado KPC, enquanto mantém o baixo consumo de potência. Para avaliar a capacidade de bombeamento do KPC, diferentes ângulos entre a raiz e a ponta das pás foram estudados. O ângulo da raiz foi mantido em 45º, enquanto o ângulo da ponta da pá foi modificado, resultando em diferentes pás. As simulações em CFD foram feitas com água e com água e areia. O modelo de turbulência utilizado foi o Shear Stress Transport (SST) e foi utilizada a técnica de simulação Sliding Grid. O modelo escolhido para as simulações foi validado experimentalmente. O descolamento da camada limite na ponta das pás dos impelidores foi visualizado, e o objetivo principal do trabalho, encontrar o impelidor KPC otimizado, foi atingido. Este impelidor possui 45º na raiz da pá e 10º na ponta da pá. O impelidor otimizado confirmou seu melhor desempenho quando comparado ao impelidor inicial na simulação de uma suspensão de areia e água / Abstract: An ideal impeller for solid suspension should provide complete suspension or homogenization consuming a minimum of energy. The flow in a stirred tank depends on impeller design, diameter and the location of impellers, vessel diameter, bottom design and internals. Computational Fluid Dynamics (CFD) is a powerful tool to predict the three dimensional flow and solids concentration distribution produced by different impellers of any geometric configuration. This study aims to improve the pumping of an axial pumping impeller, named KPC, while maintaining low power consumption. In order to evaluate the pumping capacity of the KPC impeller, differents angles between the root and the tip of the blades have been studied. The angle at the root was maintained at 45º, and the angle at the blade tip has been modified, resulting in different blades. CFD simulations were performed for water and for water and sand. The model used the Shear Stress Transport (SST) turbulence model and the Sliding Grid simulation strategy. The model was validated against experimental data. The impelller blade flow separation was visualized, and the main objective of the work, which was to find the optimized KPC impeller, was reached. This impeller possess 45º in the blade root and 10º in the tip of the blade. The optimized impeller confirmed its better performance when compared to the initial impeller in a simulation of a suspension of sand and water / Mestrado / Desenvolvimento de Processos Químicos / Mestre em Engenharia Química

A framework for understanding the fundamental physics of flowfields over forebody type shapes at low speed, high angle of attack conditions with special emphasis on sideslip has been established. Computational Fluid Dynamics (CFD) has been used to study flowfields over experimentally investigated forebodies: the Lament tangent-ogive forebody, the F-5A forebody and the Erickson chine forebody. A modified version of a current advanced code, CFL3D, was used to solve the Euler and thin-layer Navier-Stokes equations. The Navier-Stokes equations used a form of the Baldwin-Lomax turbulence model modified to account for massive crossflow separation. Using the insight provided by the solutions obtained using CFD, together with comparison with limited available data, the aerodynamics of forebodies with positive directional stability has been revealed. An unconventional way of presenting the results is used to illustrate how a positive contribution to directional stability arises. Based on this new understanding, a parametric study was then conducted to determine which shapes promote a positive contribution to directional stability. / Ph. D.

Yes / In a novel development on previous computational fluid dynamics studies, the work reported here used an Eulerian two-fluid model with the shear stress transport k–ω turbulence closure model and bubble interaction models to simulate aeration tank performance at full scale and to identify process performance issues resulting from design parameters and operating conditions. The current operating scenario was found to produce a fully developed spiral flow. Reduction of the airflow rates to the average and minimum design values led to a deterioration of the mixing conditions and formation of extended unaerated fluid regions. The influence of bubble-induced mixing on the reactor performance was further assessed via simulations of the residence time distribution of the fluid. Internal flow recirculation ensured long contact times between the phases; however, hindered axial mixing and the presence of dead zones were also identified. Finally, two optimization schemes based on modified design and operating scenarios were evaluated. The adjustment of the airflow distribution between the control zones led to improved mixing and a 20% improvement to the mass transfer coefficient. Upgrading the diffuser grid was found to be an expensive and ineffective solution, leading to worsening of the mixing conditions and yielding the lowest mass transfer coefficient compared with the other optimization schemes studied. / College of Engineering and Physical Sciences, University of Birmingham, UK

Detonation cycles are identified as an efficient alternative to the Brayton cycles used in power and propulsion applications. Rotating Detonation Engine (RDE) operating on a detonation cycle works by compressing the working fluid across a detonation wave, thereby reducing the number of compressor stages required in the thermodynamic cycle. Numerical analyses of RDEs are flexible in understanding the flow field within the RDE, however, three-dimensional analyses are expensive due to the differences in time-scale required to resolve the combustion process and flow-field. The alternate two-dimensional analyses are generally modeled with perfectly premixed fuel injection and do not capture the effects of improper mixing arising due to discrete injection of fuel and oxidizer into the chamber. To model realistic injection in a 2-D analysis, the current work uses an approach in which, a Probability Density Function (PDF) of the fuel mass fraction at the chamber inlet is extracted from a 3-D, cold-flow simulation and is used as an inlet boundary condition for fuel mass fraction in the 2-D analysis. The 2-D simulation requires only 0.4% of the CPU hours for one revolution of the detonation compared to an equivalent 3-D simulation. Using this method, a perfectly premixed RDE is comparing with a non-premixed case. The performance is found to vary between the two cases. The mean detonation velocities, time-averaged static pressure profiles are found to be similar between the two cases, while the local detonation velocities and peak pressure values vary in the non-premixed case due to local pockets fuel rich/lean mixtures. The mean detonation cell sizes are similar, but the distribution in the non-premixed case is closer due to stronger shock structures. An analytical method is used to check the effects of fuel-product stratification and heat loss from the RDE and these effects adversely affect the local detonation velocity. Overall, this method of modeling captures the complex physics in an RDE with the advantage of reduced computational cost and therefore can be used for design and diagnostic purposes. / Master of Science / The conventional Brayton cycle used in power and propulsion applications is highly optimized, at cycle and component levels. In pursuit of higher thermodynamic efficiency, detonation cycles are identified as an efficient alternative and gained increased attention in the scientific community. In a Rotating Detonation Engine (RDE), which is based on the detonation cycle, the compression of gases occurs across a shock wave. This method of achieving high compression ratios reduces the number of compressor stages required for operation. In an RDE (where combustion occurs between two coaxial cylinders), the fuel and oxidizer are injected axially into the combustion chamber where the detonation is initiated. The resultant detonation wave spins continuously in the azimuthal direction, consuming fresh fuel mixture. The combustion products expand and exhaust axially providing thrust/mechanical energy when coupled with a turbine. Numerical analyses of RDEs are flexible over experimental analysis, in terms of understanding the flow physics and the physical/chemical processes occurring within the engine. However, three-dimensional numerical analyses are computationally expansive, and therefore demanding an equivalent, efficient two-dimensional analysis. In most RDEs, fuel and oxidizer are injected from separate plenums into the chamber. This type of injection leads to inhomogeneity of the fuel-air mixture within the RDE which adversely affects the performance of the engine. The current study uses a novel method to effectively capture these physics in a 2-D numerical analysis. Furthermore, the performance of the combustor is compared between perfectly premixed injection and discrete, non-premixed injection. The method used in this work can be used for any injector design and is a powerful/efficient way to numerically analyze a Rotating Detonation Engine.

The detonation-based engine has the key advantage of increased thermodynamic efficiency over the traditional constant pressure combustor. These detonation-based engines are also known as Pressure Gain Combustion systems (PGC) and Rotating Detonation Combustor (RDC) is a form of PGC, in which the detonation wave propagates azimuthally around an annular combustor. Prior researchers have performed a high fidelity 3-D numerical simulation of a rotating detonation combustor (RDC) to understand the flow physics such as detonation wave velocity, pressure profile, wave structure; however, performing these 3-D simulations is computationally expensive. 2-D simulations are a potential alternative to reduce computational cost. In most RDCs, fuel and oxidizer are injected discretely from separate plenums, and this discrete fuel/air injection results in inhomogeneous mixing within the domain. Due to the discrete fuel injection locations, fuel/oxidizer will stratify to form localized pockets of rich and lean mixtures. The motivation of the present study is to investigate the impact of unmixedness and stratification length scales on the performance of an RDC using a 2-D numerical approach. Unmixedness, which is defined as the standard deviation of equivalence ratio normalized by the mean global equivalence ratio, is a measure of the degree of fuel-oxidizer inhomogeneity. To model the effect of unmixedness in a 2-D domain, a lognormal distribution of the fuel mass fraction is generated with a mean equivalence ratio of 1 and varying standard deviations at the inlet boundary as a numerical source term. Moreover, to model the effects of stratification length scales, fuel mass fraction at the inlet boundary cells is bundled for a given length scale, and the mass fractions for these bundles are updated based on the lognormal distribution after every three-time steps. Using this methodology, 2-D numerical analyses are carried out to investigate the performance of an RDC for an H2-air mixture with varying unmixedness and stratification length scales. Results show that mean detonation velocity decreases and wave speed variation increases with an increase in unmixedness. However, with an increase in stratification length scale mean velocity remain relatively unchanged but variation in local velocity increases. The detonation wave front corrugation also increases with an increase in mixture inhomogeneity. The mean detonation cell size increases with an increase in unmixedness. The cell shape becomes more distorted and irregular with an increase in stratification length scale and unmixedness. The combined effect of unmixedness and stratification length scale leads to a decrease in pressure gain. Overall, this concept is able to elucidate the effects of varying unmixedness and stratification length scales on the performance of an RDC. / Master of Science / Pressure Gain Combustion (PGC) system has gained significant focus in recent years due to its increased thermodynamic efficiency over a constant pressure Brayton Cycle. Rotating Detonation Combustor (RDC) is a type of PGC system, which is thermodynamically more efficient than the conventional gas turbine combustor. One of the main aspects of the detonation process is the rapid burning of the fuel-oxidizer mixture, which occurs so fast that there is not enough time for pressure to equilibrate. Therefore, the process is thermodynamically closer to a constant volume process rather than a constant pressure process. A constant volume cycle is thermodynamically more efficient than a constant pressure Brayton cycle. In an RDC, a mixture of fuel and air is injected axially, and a detonation wave propagates continuously through the circumferential section. Numerical simulation of an RDC provides additional flexibility over experiments in understanding the flow physics, detonation wave structure, and analyzing the physical and chemical processes involved in the detonation cycle. Prior researchers have utilized a full-scale 3-D numerical simulation for understanding the performance of an RDC. However, the major challenge with 3-D analyses is the computational expense. Thus, to overcome this, an inexpensive 2-D simulation is used to model the flow physics of an RDC. In most RDCs, the fuel and oxidizer are injected discretely from separate plenums. Due to the discrete fuel injection, the fuel/air mixture is never perfectly premixed and results in a stratified flow field. The objective of the current work is to develop a novel approach to independently investigate the effects of varying unmixedness and stratification length scales on RDC performance using a 2-D simulation.

Den pågående elektrifieringen av transport och samhälle kräver utveckling av nya metoder för återvinning av batterier. Hydrometallurgi som fokuserar på selektiv kristallisation av metaller är ett intressant alternativ för dessa ändamål. Dessa system kan studeras genom modellering och simulering. Många matematiska modeller finns tillgängliga för att beskriva de olika involverade processerna i kristallisationen av metaller. Dessa processer inkluderar övermättnad, nukleation, kristalltillväxt och aggregation. Denna rapport sammanställer ett antal av de tillgängliga matematiska modellerna och presenterar ett numeriskt tillvägagångssätt för modellering av den tidsberoende nummerdensiteten av partiklar genom en populationsbalansekvation. Populationsbalansen kan lösas med olika metoder såsom momentmetoden och metoden av viktade residualer. Här löses ekvationen genom diskretisering. Diskretisering av den inre koordinaten i ett flertal längdintervall möjliggör simulering av partikel-storleksfördelningen som en funktion av tid. Det numeriska tillvägagångssättet applicerades på bariumsulfatutfällning i en perfekt blandad satsreaktor och två- och tre-dimensionella T-mixer-system, såväl som en perfekt blandad satsreaktor för förträngningskristallisation av nickelsulfat med groddning. Den simulerade storleksfördelningens placering visade sig ha bra överenstämmelse med experimentell data vid låga Reynolds-tal. Här undersöktes även påverkan av en mängd parametrar såsom diskretisering, aggregation och magnituden av diffusion. Aggregation hade en märkbar inverkan på välblandade system. Inverkan av aggregation i diffusions-kontrollerade system med kort retentionstid var låg. Diffusionsmagnituden hade liten påverkan på den normaliserade distributionen men större på det totala antalet partiklar. / The currently ongoing electrification of society and transport necessitates the development of novel methods for battery recycling. Hydrometallurgy with a focus on selective metal crystallisation is an interesting prospect to these ends. The resource recovery systems of interest can be studied through simulation where many mathematical models are available to describe the varying processes involved. These processes include supersaturation generation, nucleation, growth and aggregation. This work compiles some of these mathematical models and presents a numerical approach for the modelling of the time-dependent particle number density with a population balance equation. The population balance equation can be solved using a variety of different methods such as method of moments and method of weighted residuals. Here, the balance equation was solved by discretisation. Discretising the inner coordinate (crystal length) into a number of length intervals allows for the particle size distribution to be modelled as a function of time for various crystallisation systems. The framework was successfully applied to barium sulphate precipitation in a perfectly mixed batch reactor and two- and three-dimensional T-mixer systems, as well as a seeded perfectly mixed nickel sulphate anti-solvent crystallisation system. The simulated size distribution showed promising similarity to experimental data at low Reynolds number. The influence of a variety of parameters such as aggregation and magnitude of diffusion was investigated. Aggregation had a significant impact on well-mixed systems increasing with retention time. The impact of aggregation on diffusion-controlled systems with low retention time was low. The magnitude of diffusion had little impact on the particle size distribution of the crystal population but a large impact on the total number of crystals.

Aujourd'hui divers systèmes de propulsion marins existent dont les systèmes de propulsion à jet. De nombreuses études ont été réalisées au cours des vingt dernières années et plus particulièrement par le biais de la simulation numérique ( Computational Fluid Dynamics , ( CFD )). Un modèle numérique simulant l'écoulement au travers un système de propulsion avec une pompe en rotation est développé dans ce projet. Il est également validé avec des résultats expérimentaux obtenus par d'autres chercheurs. Pour se [i.e. ce] faire, différentes étapes sont réalisées. En premier lieu, des paramètres tels que le maillage, le modèle de turbulence ou la modélisation de la rotation du rotor sont validés numériquement sur deux géométries. Le premier cas, bien documenté, correspond à un écoulement au travers une conduite en forme de"S" de section divergente et validé expérimentalement. Le second cas est une pompe où le rotor est en mouvement dans l'écoulement. Un modèle à multiple systèmes de référence ( Multiple Reference Frame,MFR ) est utilisé pour simuler la rotation de la pompe. Les paramètres numériques sont alors fixés pour la suite de l'étude. Ensuite un inodéle numérique d'un système de propulsion à jet d'une motomarine est développé dans un volume de contrôle réduit. Il prend en compte l'ensemble de la géométrie de la propulsion : la pompe en rotation, le venturi et une partie de la coque réelle du véhicule. Les conditions aux frontières sous la coque sont imposées grâce aux données d'une simulation complète du véhicule entier. Ce modèle est validé expérimentalement à deux vitesses (25 mph et 69 mph). Le comportement de l'écoulement est ensuite analysé. Finalement diverses variations géométriques sont effectuées telles que la supression [i.e. suppression] d'appendices dans la conduite ou le déplacement latéral de la lèvre de l'entrée d'eau à divers IVR, Inlet Velocity Ratio (rapport entre la vitesse du véhicule et celle de la pompe). Une augmentation des performances du système est observée à un certain IVR pour une supression [i.e. suppression] d'appendice donnée. La présence d'une plaque permettant le redressement de l'écoulement au niveau de la grille est néfaste à la poussée de même que la présence de l'arbre ou d'ailettes situées à l'entrée de la pompe. Le déplacement de la lèvre a pour objectif de déterminer la position optimale qui permet d'obtenir la meilleure augmentation de performance pour un IVR .

Depuis une vingtaine d’années, l’engouement pour les propulsions hydrojets n’a fait que croître et elles s’imposent aujourd’hui comme la propulsion marine incontournable pour les hautes vitesses. Dans un même temps, un outil permettant un gain considérable de temps et d’argent s’est lui aussi développé considérablement. En effet, la CFD (Computational Fluid Dynamics) est devenue une pratique courante lorsqu’il s’agit de prévoir le comportement d’un écoulement sans avoir à passer par un modèle réel. Elle sera utilisée tout au long du projet pour simuler le flux au travers de la propulsion. Le design d’une entrée d’eau est capital : une entrée d’eau mal conçue engendrera des zones de cavitation, de la recirculation sur la lèvre ou la rampe, des pertes importantes et un champ de vitesse non uniforme à la face de la pompe. Il en résultera une diminution du rendement de l’entrée, mais aussi une diminution du rendement de la pompe, puisqu’optmisée pour un flux uniforme. L’objectif de ce projet sera d’optimiser l’entrée d’eau pour augmenter le rendement global de la propulsion et ainsi réduire la consommation d’essence de 6 % sur un cycle donné. Actuellement, les conduites d’entrées sont conçues pour optimiser une vitesse de croisière moyenne. Dans ce projet, le but sera d’éviter d’avoir un compromis à faire entre les basses vitesses, la vitesse de croisière et la vitesse de pointe, et d’optimiser la géométrie de l’entrée pour une large plage de fonctionnement. Cela passe par une géométrie variable et donc un mécanisme asservi. Afin de concevoir un tel système, il sera nécessaire de trouver les géométries optimales pour les différents régimes de fonctionnement. Une étude CFD 2D paramétrable permettra de trouver les lignes directrices de ces géométries. Un modèle 3D devra ensuite être validé, puis utilisé pour pouvoir affiner les géométries optimales. Un système sera alors conçu puis testé sur le modèle CFD. Des tests expérimentaux viendront finaliser l’étude.