Dans le contexte actuel, l'open-rotor contrarotatif connaît un regain d'intérêt. Cependant, en l'absence de carter extérieur, la prédiction des effets d'installation devient une problématique primordiale du cycle de conception. L'objectif de ces travaux de thèse est de construire une méthode de calcul qui permette à la fois de rendre compte de l'impact du bloc moteur sur la traînée de l'avion et de l'impact de l'installation sur les performances aérodynamiques des hélices. Suite à une étude bibliographique, nous nous sommes orientés vers le couplage des codes ligne portante LPC2 et RANS elsA, développés à l'Onera. La méthode de couplage se base sur la condition de disque d'action et est itérative afin de rendre compte de l'interaction.Dans un second temps, des résultats de calculs instationnaires et d'essais en soufflerie ont été comparés aux résultats fournis par le couplage afin de confirmer que ce dernier rendait bien compte des performances aérodynamiques du moteur en configuration installée. Afin de valider sur un large domaine de calcul, plusieurs configurations ont été utilisées, prenant en compte différentes installations, différentes hélices et plusieurs points de vol.Enfin, nous avons proposé une amélioration de la condition de disque d'action par une modélisation de la turbulence représentant l'impact du passage des hélices sur l'écoulement. En effet, en l'état actuel, cette condition n'est pas en mesure de retranscrire l'impact des hélices sur la turbulence, en particulier sur l'augmentation du taux de turbulence. C'est pourquoi une formulation originale d'un modèle de turbulence, basée sur les travaux de Mr Benay, a été proposée. / The counter rotating open rotor entered a period of renewed interest because of the current circumstances. However, due to the absence of outer casing, predicting the installation's effects became an essential issue of the design process. The objective of this thesis is to elaborate a calculation method able to give the impact of the engine on the aircraft drag as well as the installation impact on the propellers aerodynamic performances. As a result of a literature review, we headed for the coupling of the LPC2 lifting-line code and elsA RANS code, developed by the Onera. The coupling method is based on the actuator disc condition and was made iterative in order to take the interaction into account.In a second phase, results from unsteady simulations and wind tunnel experiments were compared to the coupling results so as to confirm that the later was able to produce the engine's aerodynamic performances under the influence of the installation. In order to validate the coupling on a wide computational domain, multiple configurations were used, taking different installations into account, with different propellers and multiple flight conditions.Finally, an improvement of the actuator disc condition was proposed through a turbulence modeling showing the impact of the blades passages on the flow. Indeed, the actuator disc condition is currently unable to faithfully transpose the propellers impact on the turbulence, especially on the turbulence rate increase. Therefore, an original formulation of a turbulence model was given, based on the works of Mr. Benay.

La ventilation joue un rôle important dans le confort thermique des occupants d'un bâtiment en climat chaud, en contribuant au rafraîchissement de l'air qui les entoure. Qu'elle soit mécanique ou naturelle, la ventilation doit être maîtrisée pour ne pas gêner l'occupant et respecter des normes ou réglementations en vigueur. Ces gênes sont liées à des vitesses d'air ou à une intensité turbulente trop élevée. Les concepteurs doivent alors faire appel à l'outil numérique pour une prédiction fine des écoulements d'air. La simulation de configurations à l'échelle du bâtiment peut se faire par une approche moyennée des équations de Navier-Stokes en complément d'un modèle de turbulence. Ces simulations sont utilisées par les chercheurs comme des outils de dimensionnement, ou encore, d'optimisation des composants de ventilation. De plus, la forme des bouches de ventilation peut contribuer passivement à l'optimisation de certains phénomènes aérauliques. L'amélioration de ces formes peut ainsi se faire par l'utilisation de méthodes d'optimisation de forme. L'optimisation topologique par ajout de matière permet de trouver des formes pour optimiser des fonctionnelles objectifs définies sur le fluide ou sur ses frontières. C'est sur cette méthode que ces travaux de thèse se concentrent pour proposer un outil de contrôle des écoulements d'air dans le bâtiment par la recherche de formes optimales de bouches de ventilation. Ces travaux de thèse proposent une contribution à l'optimisation topologique d'écoulements turbulents dans le bâtiment. Dans un premier temps, la méthode par ajout de matière est appliquée pour minimiser les pertes de charge dans une conduite d'aération en forme de Té. Le modèle adjoint développé est soumis à l'hypothèse de turbulence gelée. Dans un second temps le modèle adjoint complet est proposé pour le modèle de turbulence standard k-epsilon pour la réduction des pertes de charge d'une part et de l'intensité turbulente d'autre part. Enfin, ces outils sont appliqués à l'optimisation de forme de bouches de ventilation. Les résultats montrent ainsi un bon potentiel de l'optimisation topologique par ajout de matière pour l'orientation des écoulements d'air mais ne garantissent pas la maîtrise des vitesses d'air dans la pièce. De plus, la minimisation de l'intensité turbulente grâce à l'approche complète développée a contribué à la réduction du taux d'insatisfaction lié à une intensité turbulente trop élevée dans la pièce. / Ventilation plays a key role in thermal comfort of building's occupants in hot climates by refreshing air surrounding them. Mechanical or natural ventilation must be controlled for two reasons: do not disturb the bulding's occupants and comply with the regulations in force. Discomfort is linked to too high air velocities or turbulent intensity. Designers can use the numerical tools for a finer prediction of airflow. The simulation of configurations at the building scale can be done using averaged Navier-Stokes equations approach in addition to a turbulence model. These simulations are used by researchers as sizing tools or for the optimization of ventilation components. In addition, the shape of the ventilation nozzle can passively contributes to the optimization of some aeraulics phenomena. The improvement of these ventilation components can be achieved by the use of shape optimization methods. Topological optimization by addition of material makes it possible for the optimization of cost functions defined on the fluid or on its boundaries. The main objective of this manuscript is to propose a tool to control airflows in building by the search for optimal shape of ventilation nozzle. This work proposes a contribution to the topological optimization of turbulent flows in buildings. In a first step, topological optimization by adding material is applied to minimize pressure losses in a T-shaped pipe. The developed model is subjected to the hypothesis of the frozen turbulence. In a second step, the complete adjoint model is proposed for the standard turbulence model k-epsilon for the minimization of the total pressure losses on the one hand and the turbulent intensity on the other hand. Finally, these tools are applied to the shape optimization of ventilation nozzle. The results of topological optimization by adding virtual material show good potential for the orientation of the airflows but does not guarantee the control of the air velocities in the room. Moreover, the minimization of turbulent intensity through the complete approach contributed to the reduction of the dissatisfaction rate due to excessive turbulent intensity in the room.

La pollution atmosphérique et ses conséquences sur la santé et l'environnement constituent un domaine d'étude complexe à cause du nombre de phénomènes physiques mis en jeu. L'objectif de ce travail est d'étudier les principales caractéristiques de l'écoulement et de la dispersion d'un scalaire passif au sein de la canopée urbaine. Pour ce faire, un code numérique a été développé. Il résout les équations de Navier-Stokes dans le cadre d'un écoulement incompressible pour une atmosphère neutre en faisant usage de la méthode de la compressibilité artificielle selon la méthode des volumes finis. Le modèle de Spalart-Allmaras a été utilisé pour la modélisation de la turbulence. La canopée urbaine est explicitement prise en compte et est modélisée par un groupe d'obstacles de forme cubique. Le code fut d'abord testé pour des configurations bidimensionnelles avec un seul et 4 obstacles en configuration alignée selon deux approches : une simulation stationnaire RANS et instationnaire URANS qui reproduit le décrochement tourbillonnaire. La prise en compte du décrochement tourbillonnaire se traduit par une diffusion dans le sillage turbulent du groupe d'obstacles. Les résultats ont été comparés à des mesures expérimentales et d'autres résultats numériques de référence dans la bibliographie et montrent l'amélioration du champ de vitesse moyen par l'approche code fut ensuite testé sur un cas tridimensionnel avec un groupe d'obstacles organisés selon 2 configurations géométriques: alignée et en quinconce. Afin d'éliminer les effets des conditions aux limites, l'écoulement fut calculé sur un volume élémentaire de calcul en utilisant des conditions aux limites périodiques. Deux types de simulations furent réalisés: l'approche RANS classique et la version DDES du modèle de Spalart-Allmaras. L'écoulement obtenu par la DDES améliore de façon significative les résultats par rapport au RANS en comparaison de mesures expérimentales de simulation directe et montrent la bonne potentialité du modèle. La dispersion d'un scalaire passif émis au sein de la canopée fut obtenue sur un domaine plus important comprenant 16 volumes élémentaires par le biais des conditions aux limites périodiques utilisées. Une analyse du champ de concentration a ensuite été réalisée et des comparaisons effectuées en fonction du type de calcul et de la configuration géométrique. / Atmospheric pollution and its impact on health and the environment depend on many physical phenomena, and this makes it a difficult subject to study. The main objective of this work is to investigate the main characteristics of the flow and dispersion of a passive scalar in the urban canopy. Specifically, the urban canopy is simulated by a group of cubical obstacles in a neutrally-buoyant atmospheric boundary layer. A numerical code bas been developed as a tool to aid in this study; flow is computed by solving the Navier-Stokes equations for an incompressible flow, using a finite volume approach, and the method of artificial compressibility. The turbulence is modeled using the method proposed by Spalart and Allmaras. The code was tested first in a 2-D configuration, for flow over a single obstacle, and over a group of 4 obstacles; in both cases two types of simulation were studied: a stationary RANS simulation, and an unsteady RANS (URANS), which reproduced vortex shedding from the obstacles. The explicit inclusion of vortex shedding in the URANS simulation leads to diffusion in the obstacle wakes, and the results compare better with experimental measurements and other published numerical simulations than do those for the RANS simulations. The code was then tested for some 3-D cases consisting of a group of obstacles arrangcd either in aligned or staggered configurations. In order to avoid the influence of boundary conditions, the flow field was simulated using periodic boundary conditions and a small sub-unit from the group of obstacles. Two types of simulation were performed: a classical RANS type calculation and the DDES proposed by Spalart and Allmaras. The results obtained using the ODES agree much more closely with experimental measurements and the results of other numerical simulations than do those obtained using RANS, and indicate the potential of this approach. The dispersion of a passive scalar in the urban canopy was simulated on a much larger domain consisting of 16 of the sub-units used to compute the flow field. The concentration fields were analyzed to show the influence of the geometrical configuration and the type of model.

La simulation des grandes échelles (SGE ou LES pour large eddy simulation) commence à être très utilisée dans l’industrie. Par résolution directe des structures turbulents de grande tailles, le calcul LES est capable de calculer le bruit générée par la voilure ou de prédire avec précision le décollement de coin dans une configuration très simplifiée du compresseur. L’un des problèmes les plus importants pour effectuer un calcul LES est de fournir des conditions d’entrée avec des champs turbulents.Pour une approche hybride RANS/LES (RANS pour Reynolds Averaged Navier-Stokes), les conditions d’entrée turbulentes pour un calcul LES sont générées à l’aide des solutions fournies par le calcul RANS en amont. Il existe plusieurs méthodes pour générer les conditions d’entrée pour LES. Elles peuvent principalement être classées en deux catégories : 1) simulation avec pré-calcul ; 2) la méthode de turbulence synthétique. La simulation avec pré-calcul consiste à effectuer un calcul LES indépendant pour générer un champ turbulent comme conditions d’entrée pour alimenter le calcul principal. Cette méthode peut obtenir des turbulences de haute qualité, mais elle augmente considérablement le temps de calcul et le stockage des données. Le champ turbulent généré par la méthode de turbulence synthétique exige une « distance de adaptation », pendante laquelle le champ turbulent devient pleinement développé. L’objectif principal pour améliorer ce genre de méthodes est donc de diminuer cette distance nécessaire.Dans cette thèse, la méthode de vortex, qui est une approche de turbulence synthétique, est présentée et améliorée. A travers des expériences numériques, les paramètres de la méthode de vortex améliorée sont systématiquement optimisés. L’application à l’écoulement en canal plan et à couche limite en plaque plane, montrent que la méthode de vortex améliorée génère de manière efficace pour fournir des conditions d’entrée pour LES. Dans le cas de l’écoulement en canal plan, la distance d’adaptation nécessaire pour le rétablissement de la turbulence est d’environ 6 fois la demi-hauteur du canal. Pour le cas de l’écoulement en plaque plane, cette distance est environ 21 fois l’épaisseur de la couche limite. Enfin, dans le but de qualifier la turbulence obtenue par des calculs LES, nous utilisons les coefficients de dissymétrie des dérivées des fluctuations de vitesse, et, nous les introduisons comme un nouveau critère pour la qualité de LES. / Large eddy simulation is becoming an important numerical tool in industry recently. Resolving large scale turbulent motions directly, LES is capable to compute the aeroacoustic noise generated by the airfoil or to precisely capture the corner separation in a linear compressor cascade. The main challenge to perform a LES calculation is to prescribe a realistic unsteady inflow field. For hybrid RANS/LES approaches, inflow conditions for downstream LES region must be generated from the upstream RANS solutions. There exist several methods to generate inflow conditions for LES. They can mainly be divided into two categories: 1) Precursor simulation; 2) Synthetic turbulence methods. Precursor simulation requires to run a separate calculation to generate a turbulent ow or a database to feed the main computation. This kind of methods can generate high quality turbulence. However, it requires heavy extra computing load. Synthetic turbulence methods consist in generating a fluctuating velocity field, and within a short “adaptation distance”, the field get fully developed. So main goal of synthetic turbulence methods is to decrease the required adaptation distance. The vortex method which is a synthetic turbulence method is presented and improved here. Parameters of the improved vortex method are optimized systematically with a series of calculations in this thesis. Applications on channel and flat-plate flows show that the improved vortex method is effective in generating the LES inflow conditions. The adaptation distance required for turbulence recovery is about 6 times the half channel height for channel flow, and 21 times the boundary-layer thickness (at the inlet of vortex) for at-plate ow. The velocity-derivative skewness is used to qualify the generated turbulence, and is introduced as a new criterion of LES calculation.

A reinforced fiber-glass model of a NACA 4412 wing profile is designed and set-up in the Minimum Turbulence Level (MTL) wind tunnel facility at KTH. The model has 65 pressure taps orifices, and the set-up includes two mounting panels designed to allow for particle image velocimetry (PIV) and hot wire anemometry (HWA) measurements of the boundary layer (to be performed in a future campaign). In a first experimental campaign pressure scans are conducted at three angles of attack of interest (5,10 and 12 degrees), and at four different Reynolds numbers based on chord length and inflow velocity (200,000, 400,000, 1,000,000, and 1,640,000). The preliminary results show good agreement with DNS and LES data, however, the effective angle of attack of the wing is affected by the interference of the test section. In order to obtain proper flow conditions for future campaigns inside the test section, wall inserts are designed using 2D k-omega SST simulations. The side-walls are streamlined and the final geometry is corrected to account for the boundary-layer growth over them. The inserts are shown to avoid early separation near the trailing edge at higher angles of attack (10 and 12 degrees), but the 2D simulations fail to capture the aforementioned angle-of-attack issue affecting the pressure distributions. Future extensions of the present insert design should include both 3D simulations of the test-section and a robust optimization procedure to prescribe the resulting pressure distribution. / En NACA 4412 vingprofilsmodel av förstärkt glasfiber utformas och installeras enligt Minimum Turbulence Level (MTL) i vindtunnelanläggningen på KTH. Modellen har 65 tryckluftsöppningar, och uppsättningen innehåller två monteringspaneler som är utformade för att möjliggöra mätningar av particle image velocimetry (PIV) and hot wire anemometry (HWA) hos gränsskiktet (som ska utföras i en framtida kampanj). I en första experimentell kampanj utförs tryckskanningar vid tre anfallsvinklar av intresse (5, 10, och 12 grader) samt vid fyra olika Reynolds-nummer (200 000, 400 000, 1 000 000 och 1 640 000). De preliminära resultaten visar god överensstämmelse med DNS- och LES-data, men den effektiva anfallsvinkeln på vingen påverkas av störningar från testsektionen. För att tillhandahålla korrekta flödesförhållanden för framtida kampanjer i testdelen är vägginsatser konstruerade med 2D k-omega SST-simuleringar. Sidoväggarna är strömlinjeformade och den slutliga geometrin korrigeras för att ta hänsyn till gränsiktets tillväxt. Insatserna undviker den tidig separation som sker nära bakkanten vid högre anfallsvinklar (10 och 12 grader), men 2D-simuleringarna misslyckades med att fånga det ovan nämnda anfallsvinkelproblemet som påverkar tryckfördelningarna.

[pt] Modelos RANS (Reynolds Average Navier-Stokes) estão entre os modelos mais empregados para resolver escoamentos turbulentos, devido a seu baixo custo computacional. A maioria dos modelos RANS usa a aproximação de Boussinesq, baseada em uma relação linear entre a parte deviatórica do tensor de Reynolds e o tensor taxa de deformação, com a viscosidade turbulenta sendo o parâmetro positivo de proporcionalidade. Contudo, esses modelos falham em várias situações, e um grande esforço tem sido feito pela comunidade científica com intuito de melhorar a previsibilidade do modelo desenvolvendo modelos não lineares. Análises de modelos de ordem superior empregando tensores ortogonais objetivos têm mostrado que estes são muito promissores para melhorar a previsão dos componentes normais do tensor de Reynolds. No presente trabalho, modelos não lineares baseados no quadrado do tensor taxa de deformação e no tensor não persistência de deformação foram avaliados para uma faixa de número de Reynolds baseados na velocidade de atrito, variando de 395 até 5200. Novas funções de parede foram desenvolvidas, utilizando energia cinética turbulenta e o módulo do tensor taxa de deformação para determinar a velocidade e comprimento característicos. Além disso, um novo modelo turbulento de uma-equação baseado somente na equação de transporte da energia cinética turbulenta foi proposto juntamente com uma equação de fechamento algébrica para modelar a dissipação da energia cinética turbulenta. Os resultados dos modelos para escoamento em canal foram comparados com os dados DNS, apresentando uma melhor aderência aos dados DNS em comparação com os resultados de outros modelos RANS encontrados na literatura. / [en] Reynolds Average Navier Stokes (RANS) models are among the most employed models to solve turbulent flows, due to their low computational cost. The majority of RANS models use the Boussinesq approximation, based on a linear relation between the deviatoric part of Reynolds stress tensor and the rate of strain tensor, with the turbulent viscosity as the positive proportionality parameter. However, these models fail in several situations, and a great deal of effort has been made by the scientific community aiming to improve model prediction through the development of non-linear models. Analysis of higher-order models employing objective orthogonal tensors has shown that these are very promising to improve the prediction of the normal components of the Reynolds stress. In this work, non-linear models based on the square of the rate-strain tensor and non-persistence tensor were examined for a range of friction Reynolds number from 395 to 5200. New wall damping functions were developed, employing the turbulent kinetic energy and intensity of the rate of strain tensor to determine the turbulent characteristic velocity and length. Further, a new one-equation turbulent model based only on the turbulent kinetic energy transport equation was proposed coupled with an algebraic closure equation to model the turbulent kinetic energy dissipation. The models prediction for a channel flow were compared with DNS data and presented a better adherence to the DNS data, than the results of other RANS models available in the literature.

The use of turbocharged Diesel engines is nowadays a widespread practice in the automotive sector: heavy-duty vehicles like trucks or buses, in particular, are often equipped with turbocharged engines. An accurate study of the flow field developing inside both the main components of a turbocharger, i.e. compressor and turbine, is therefore necessary: the synergistic use of CFD simulations and experimental tests allows to fulfill this requirement. The aim of this thesis is to investigate the performance and the flow field that develops inside a centrifugal compressor for automotive turbochargers. The study is carried out by means of numerical simulations, both steady-state and transient, based on RANS models (Reynolds Averaged Navier-Stokes equations). The code utilized for the numerical simulations is Ansys CFX.   The first part of the work is an engineering attempt to develop a CFD method for predicting the performance of a centrifugal compressor which is based solely on steady-state RANS models. The results obtained are then compared with experimental observations. The study continues with an analysis of the sensitivity of the developed CFD method to different parameters: influence of both position and model used for the rotor-stator interfaces and the axial tip-clearance on the global performances is studied and quantified.   In the second part, a design optimization study based on the Design of Experiments (DoE) approach is performed. In detail, transient RANS simulations are used to identify which geometry of the recirculation cavity hollowed inside the compressor shroud (ported shroud design) allows to mitigate the backflow that appears at low mass-flow rates. Backflow can be observed when the operational point of the compressor is suddenly moved from design to surge conditions. On actual heavy-duty vehicles, these conditions may arise when a rapid gear shift is performed. / Användningen av turboladdade dieselmotorer ärr numera utbredd inom bilindustrin: i synnerhet tunga fordon som lastbilar eller bussar ärr ofta utrustade med turbo-laddade motorer. En utförlig förståelse av flödesfältet som utvecklas innuti båda huvudkomponenterna hos en turboladdare, dvs kompressor och turbin, är därför nödvändig: den synergistiska användningen av CFD-simuleringar och experimentel-la tester möjliggör att detta krav uppfylls. Syftet med denna avhandling är att undersöka prestanda och det flödesfält som utvecklas i en centrifugalkompressor för turboladdare. Studien utförs genom nu-meriska simuleringar, både steady state och transient, baserat på RANS-modeller (Reynolds Averaged Navier-Stokes-ekvationer). Koden som används för de numeriska simuleringarna är Ansys CFX.   Den första delen av arbetet ¨ar ett försöka att utveckla en CFD-metod för att förutsäga prestanda för en centrifugalkompressor med hjälp av steady-state RANS-modeller. De erhållna resultaten jämförs sedan med experimentella observationer. Studien fortsätter med en analys av känsligheten hos den utvecklade CFD-metoden till olika parametrar: Inflytande av både position och modell som används för rotor-statorgränssnitt samt axiellt spel mellan rotor och hus på de globala prestationerna studeras och kvantifieras.   I andra delen utförs en designoptimeringsstudie baserad på Design of Experiments (DoE). I detalj används tidsupplösta RANS-simuleringar för att identifiera vilken utformning av ported shroud som minskar backflöde i kompressorn under en snabb minskning av massflöde och varvtal och därmed ger bättre prestanda i transient surge. På tunga fordon kan dessa förhållanden uppstå under växling.

In axial compressor, corner separation phenomenon can occur between the blade surface and the hub. This leads to high total pressure losses, blockage and may worsen to surge. Various studies on NACA65-009 blade were previously performed experimentally and numerically to predict the corner separation. The LMFA showed that RANS simulations tend to overestimate it while the Wall-Resolved LES (WRLES) was able to well capture it. The conclusions drawn on RANS are validated here with another solver software. An extensive parametric study is performed on RANS which highlights the good performance of two non-linear turbulence models k − ω Wilcox QCR and EARSM k − kl for for predicting the topology and the intensity of corner separation. They are however very dependent on the mesh and the numerics. A Wall-Modeled LES (WMLES) is then computed. It reproduces well the topology of the separation given by the experiments and predicts similar anisotropy to the WRLES. Nevertheless it shows high sensitivity to the level of turbulence close to the endwall and the boundary layer profile of the upstream flow. Finally, this confirms that the WMLES is a promising alternative to the WRLES in order to study the corner separation on more costly geometries (several blades for instance). / I axiell kompressor kan hörnseparationsfenomen uppstå mellan bladytan och navet. Konsekvenserna är stora totala tryckförluster och kompressor blockering. Olika studier på NACA65-009 bladet utfördes tidigare experimentellt och numeriskt för att förutsäga hörnseparationen. LMFA visade att RANS simuleringar tenderar att överskatta den hörnseparationen medan Vägg-Löst LES (WRLES på engelska) kunde fånga bra den. Slutsatserna som dras om RANS valideras här med en annan lösningsprogramvara. En omfattande parametrisk studie utförs på RANS som belyserde goda prestandan för två icke-linjära turbulensmodeller k − ω Wilcox QCRoch EARSM k − kl för att förutsäga topologin och intensiteten för hörnseparation. Dock är de mycket beroende av nät och numerik. En Vägg-Modell LES (WMLES på engelska) beräknas sedan. Det reproducerar väl topologin för separationen som ges av experimenten och förutsäger liknande anisotropi som WRLES. Dock visar det hög känslighet för turbulensnivån nära ändväggen och gränsskiktsprofilen för uppströmsflödet. Slutligen bekräftar detta att WMLES är ett lovande alternativ till WRLES för att studera hörnseparationen på dyrare geometrier (till exempelflera blad).

This study has investigated the conceptual feasibility of a rocket propelled kinetic energy penetrator (KEP), designed for the handheld recoilless rifle Carl-Gustaf® 84 mm calibre system, from an exterior ballistics perspective. The methodology is based upon evaluating the aerodynamic properties of different conceptual design proposals through CFD-simulations and then performing trajectory analysis to assess their exterior ballistic performance. In particular, the main focus has been to optimize the stability, velocity and spin rate of the KEP. The results of the study indicates that the final chosen KEP design retains, from an aerodynamic perspective, longitudinal stability for Mach numbers up to 4.5, regardless if the rocket motor is ignited or not. Furthermore, if using NK1384 propellant, the final chosen design in the study is, according to the calculations, able to achieve a maximum velocity of 0.7⋅v_ref and retain a minimum velocity of 0.628⋅v_ref in the horizontal range of [0.318⋅x_ref,0.648⋅x_ref] measured from the shooter. In addition, the angular spin velocity achieves a maximum value of 15.5 Hz, satisfying the performance limitation of the rocket motor which only functions properly for frequencies up to 30 Hz, while simultaneously providing a sufficiently considered spin rate in order to average possible thrust and mass deviations of the KEP. The results also show that if using ammonium dinitramide (ADN) propellant, the KEP is able to achieve a maximum velocity of 0.786⋅v_ref, retain a minimum velocity of 0.628⋅v_ref in the horizontal range of [0.28⋅x_ref,0.98⋅x_ref] and achieve a maximum spin rate of 17.5 Hz. / Den här studien har på ett konceptuellt plan undersökt om det är möjligt att konstruera en raketdriven kinetisk energi-pil (KE-pil), designad för det rekylfria Carl-Gustaf® 84 mm granatgeväret. Studiens metod grundade sig i att undersöka olika konceptuella designförslag och utvärdera deras aerodynamiska egenskaper genom CFD-simulationer för att sedan genomföra bansimuleringar och bedöma deras ytterballistiska prestanda. Framför allt fokuserades det på att optimera KE-pilens stabilitet, hastighet och rollvinkelfrekvens. Resultaten från studien indikerar att det ur ett aerodynamiskt perspektiv är möjligt att statiskt stabilisera KE-pilen för Machtal upp till 4.5, oavsett om raketmotorn är antänd eller ej. Vidare, vid implementering av NK1384-krut lyder prestandaspecifikationerna enligt följande för studiens slutgiltiga designförslag enligt genomförda beräkningar. Den maximalt uppnådda hastigheten är 0.7⋅v_ref och en minimumhastighet om 0.628⋅v_ref kan upprätthållas inom det horisontella intervallet [0.318⋅x_ref,0.648⋅x_ref ] räknat ifrån skytten. Vidare uppnås en maximal rollvinkelfrekvens på 15.5 Hz, vilket tillfredsställer raketmotorns prestandabegränsning om en maximal rollvinkelfrekvens på 30 Hz, samtidigt som detta är en god frekvens för att utjämna eventuella avvikelser från raketmotors avsedda massflödesriktning tillika avsedd massdistribution hos KE-pilen. Om krutet i stället byts ut till ammoniumdinitramid (ADN) kan en maximal hastighet om 0.786⋅v_ref uppnås, en minimumhastighet om 0.628⋅v_ref kan upprätthållas inom intervallet [0.28⋅x_ref,0.98⋅x_ref ] och den maximala rollfrekvensen är 17.5 Hz.

The aerodynamics of modern rotorcraft is highly complex and has proven to be an arduous challenge for computational fluid dynamics (CFD). Flow features such as massively separated boundary layers or transition to turbulence are common in engineering applications and need to be accurately captured in order to predict the vehicle performance. The recent advances in numerical methods and turbulence modeling have resolved each of these issues independent of the other. First, state-of-the-art hybrid RANS-LES turbulence closures have shown great promise in capturing the unsteady flow details and integrated performance quantities for stalled flows. Similarly, the correlation-based transition model of Langtry and Menter has been successfully applied to a wide range of applications involving attached or mildly separated flows. However, there still lacks a unified approach that can tackle massively separated flows in the transitional flow region. In this effort, the two approaches have been combined and expended to yield a methodology capable of accurately predicting the features in these highly complex unsteady turbulent flows at a reasonable computational cost. Comparisons are evaluated on several cases, including a transitional flat plate, circular cylinder in crossflow and NACA 63-415 wing. Cost and accuracy correlations with URANS and prior hybrid URANS-LES approaches with and without transition modeling indicate that this new method can capture both separation and transition more accurately and cost effectively. This new turbulence approach has been applied to the study of wings in the reverse flow regime. The flight envelope of modern helicopters has increased significantly over the last few decades, with design concepts now reaching advance ratios up to μ = 1. In these extreme conditions, the freestream velocity exceeds the rotational speed of the blades, and a large region of the retreating side of the rotor disk experiences reverse flow. For a conventional airfoil with a sharp trailing edge, the reverse flow regime is generally characterized by massive boundary layer separation and bluff body vortex shedding. This complex aerodynamic environment has been utilized to evaluate the new hybrid transitional approach. The assessment has proven the efficiency of the new hybrid model, and it has provided a transformative advancement to the modeling of dynamic stall.