Although it is possible to directly solve an entire flow-acoustics problem in one computation, this approach remains prohibitively large in terms of the computational resource required for most practical applications. Aeroacoustic problems are therefore usually split into two parts; one consisting of the source computation and one of the source propagation. Although both these parts entail great challenges on the computational method, in terms of accuracy and efficiency, it is still better than the direct solution alternative. The source usually consists of highly turbulent flows, which for most cases will need to be, at least partly, resolved. Then, acoustic waves generated by these sources often have to be propagated for long distances compared to the wavelength and might be subjected to scattering by solid objects or convective effects by the flow. Numerical methods used solve these problems therefore have to possess low dispersion and dissipation error qualities for the solution to be accurate and resource efficient. The wave expansion method (WEM) is an efficient discretization technique, which is used for wave propagation problems. The method uses fundamental solutions to the wave operator in the discretization procedure and will thus produce accurate results at two to three points per wavelength. This thesis presents a method that uses the WEM in an aeroacoustic context. Addressing the propagation of acoustic waves and transfer of sources from flow to acoustic simulations. The proposed computational procedure is applied to a co-rotating vortex pair and a cylinder in cross-flow. Overall, the computed results agree well with analytical solutions. Although the WEM is efficient in terms of the spatial discretization, the procedure requires that a Moore-Penrose pseudo-inverse is evaluated at each unique node-neighbour stencil in the grid. This evaluation significantly slows the procedure. In this thesis, a method with a regular grid is explored to speed-up this process. / <p>QC 20161121</p>

The successful application of Computational Aeroacoustics (CAA) requires high accuracy numerical schemes with good dissipation and dispersion characteristics. Unstructured meshes have a greater geometrical flexibility than existing high order structured mesh methods. This work investigates the suitability of unstructured mesh techniques by computing a two-dimensionallinearised Euler problem with various discretisation schemes and different mesh types. The goal of the present work is the development of an unstructured numerical method with the high accuracy, low dissipation and low dispersion required to be an effective tool in the study of aeroacoustics. The suitability of the unstructured method is investigated using aeroacoustic test cases taken from CAA Benchmark Workshop proceedings. Comparisons are made with exact solutions and a high order structured method. The higher order structured method was based upon a standard central differencing spatial discretisation. For the unstructured method a vertex-based data structure is employed. A median-dual control volume is used for the finite volume approximation with the option of using a Green-Gauss gradient approximation technique or a Least Squares approximation. The temporal discretisation used for both the structured and unstructured numerical methods is an explicit Runge-Kutta method with local timestepping. For the unstructured method, the gradient approximation technique is used to compute gradients at each vertex, these are then used to reconstruct the fluxes at the control volume faces. The unstructured mesh types used to evaluate the numerical method include semi-structured and purely unstructured triangular meshes. The semi-structured meshes were created directly from the associated structured mesh. The purely unstructured meshes were created using a commercial paving algorithm. The Least Squares method has the potential to allow high order reconstruction. Results show that a Weighted Least gradient approximation gives better solutions than unweighted and Green-Gauss gradient computation. The solutions are of acceptable accuracy on these problems with the absolute error of the unstructured method approaching that of a high order structured solution on an equivalent mesh for specific aeroacoustic scenarios.

Cette thèse propose une modélisation du bruit d'origine aérodynamique, avec une attention particulière aux mécanismes de transfert d'énergie entre l'écoulement et le milieu de propagation. Une première partie aborde le problème de la création et du transport de l'énergie acoustique en milieu aérodynamique. Trois grands courants de pensée sont identifiés : l'approche eulérienne linéarise les équations valables en cas de fluide parfait pour former une loi de conservation ; l'approche dissipative développe les équations de Navier-Stokes, fait intervenir les fluctuations de vorticité comment moteur du mouvement acoustique ou décompose la quantité de mouvement en une théorie potentielle ; l'approche lagrangienne décrit le déplacement lagrangien de la perturbation qui suit le passage de l'onde acoustique. La première est la plus naturelle. La deuxième est la plus complète et la seule à expliquer la création d'énergie par l'aérodynamique. Une théorie générale voyant l'acoustique comme le seul champ généralisé qui se trouve piégé par l'aérodynamique en découle. La dernière est la plus prometteuse pour l'avenir. Dans une deuxième partie, les moyens permettant le calcul du champ acoustique à partir d'une sollicitation surfacique sont présentés. Il s'agit de la méthode d'extrapolation des ondes de Kirchhoff basée sur la pression, la formulation de Ffowcs-Williams & Hawkings basée sur les débits, et l'intégrale de Rayleigh basée sur une vitesse vibratoire. Une troisième partie de la thèse utilise les formalismes d'excitation surfacique pour étudier la réaction du milieu acoustique à des excitations génériques sous formes de paquets d'onde, représentatives de l'aérodynamique instationnaire. La réponse acoustique est caractérisée par la direction d'émission privilégiée du rayonnement et son efficacité, défini comme le taux de transfert d'énergie entre l'excitation et son milieu. On montre notamment que l'introduction d'une dissymétrie amont-aval dans l'excitation augmente fortement son efficacité, de même que la prise en compte d'un milieu de propagation en mouvement uniforme. Dans une dernière partie, ces considérations sont étendues au rayonnement d'une couche de mélange et adaptées en se basant sur l'analogie de Liepmann. Cette approche peu répandue est une intégrale de Rayleigh dont l'excitation est la dérivée temporelle de l'épaisseur de déplacement. Les résultats sont comparés avec la base de données d'une simulation acoustique directe et des deux autres méthodes surfaciques. La directivité n'est pas retrouvée par la modélisation proposée. On montre que la prédiction des niveaux nécessite de modéliser une impédance de rayonnement. / This study proposes a model for the noise generated aerodynamically, while focusing on energy transfer mechanisms between the main flow and the propagating medium. Energy harvest in aerodynamic condition is therefore the subject of a first part. Three general trends may be identified ; the eulerian approach uses linearized Euler's equations for inviscid flows in a form of a conservation law ; the dissipating approach expands Navier-Stokes equations in series, relies on vorticity fluctuations to excite the medium or splits velocity or momentum vectors in a general potential theory ; the lagrangian approach describes the lagrangian displacement of the perturbation inherent to an acoustic wave. The first approach is the most commonly adopted. The second one is the most complete and provides aerodynamical mechanisms for energy generation. A general fashion follows where acoustics is a generalized field, trapped by a hydrodynamic impedance. The last one may be subject of close attention for future considerations. In a second part, computational models are presented with their ability to predict acoustic radiation from a surface excitation. These are the Kirchhoff formalism based on the pressure, the Ffowcs Williams & Hawkings formalism based on the mass flow rate and the Rayleigh integral based on the vibration velocity. These are applied in a third part of the study to investigate the response of the acoustic medium to a generique excitation in the form of a wavepacket, representative of unsteady aerodynamics. Such acoustic response is caracterised by its direction of maximum radiation and its efficiency, defined as the rate of energy transfer between the excitation and its surrounding medium. Introducing an upstream-downstream asymmetry in the excitation is showed to significantly enhance its efficiency, as well as a convection velocity in the propagating medium. Within these general considerations, the last part of this study models acoustic excitation in a mixing layer flow based on Liepmann's analogy. This relatively unexplored theory consists in a Rayleigh integral excited by the temporal derivative of the displacement thickness. Results are compared with direct noise computation database and two other methods of surface excitation. Directivity is likely to be found while pressure amplitude is correctly predicted by using a model for radiation impedance.

Tanto os motores turbo-jato quanto os turbo-fan, são os maiores responsáveis pela geração de ruído durante a decolagem, segmento de subida e de aceleração de uma aeronave. Devido a isto, o problema de ruído em jatos vem sendo intensamente investigado ao longo dos últimos anos. Já na fase do pouso, o slat é uma das fontes de ruído mais importantes. Para este caso, na maioria das aplicações práticas, existe o descolamento da camada limite no intradorso do slat a partir de onde se desenvolve uma camada de mistura. Ainda assim, existem inúmeros aspectos de tais escoamentos que precisam de investigação. Uma abordagem frequentemente feita para o estudo da instabilidade hidrodinâmica e ruído em jatos é o estudo de metade do jato. A estratégia consiste em estudar os fenômenos na camada de mistura, o que é uma aproximação razoável quando o jato tem diâmetro muito grande comparado à espessura da camada cisalhante que se desenvolve nas bordas do jato. Assim, alguns aspectos do ruído gerado pelos modos axi-simétricos de instabilidade são em grande parte reproduzidos. Um aspecto aparentemente jamais estudado antes é o efeito do emparelhamento de vórtices de diferentes geometrias na camada de mistura. Caso o efeito da modulação dos vórtices produzisse um padrão de ruído com características diferentes no emparelhamento, um controle ativo de escoamento por excitação periódica poderia ser usado para reduzir o ruído em jatos. O objetivo do presente trabalho é investigar tal efeito. A idéia é investigar este emparelhamento de vórtices na camada de mistura em desenvolvimento temporal bi-dimensional. Com isto foi possível visualizar um emparelhamento isolado de outros emparelhamentos e sem o efeito Doppler (presente na camada de mistura em desenvolvimento espacial). O método adotado foi a simulação numérica direta (DNS) das equações de Navier Stokes compressíveis na forma não-conservativa escritas na formulação característica. Os resultados mostram que a modulação dos vórtices não produz alteração significativa do ruído gerado no emparelhamento. / Turbo-fan and turbo-jet engines are the most important noise sources during the aircraft take off, climb and acceleration segments. Owing to this fact, the jet flow noise has been studied in the past years. For the landing stage, the slat is an important sound source. In this case, the slat leading edge frequently experiences a boundary layer deattachment causing the development of a mixing layer inside the slot. Nevertheless, there are many aspects of such phenomenon that have not been studied yet. Mixing layers constitutes an usual approach for jet flow instability in aeroacoustics studies. The stategy is to study the mixing layer in order to understand the jet-flow. This strategy becomes better as the ratio between the jet diameter and mixing layer thickness becomes larger. This approach is only reazonable for the jet flow axi-symetric unstable modes. The effect of vortex modulation on the vortex pairing sound production has not been found in the literature. If such effect could cause a significant change in the sound generation patterns, an active flow control system could be developed in order to enhance the jet noise performance. The purpose of the present work was to investigate such effect. It was also possible to observe a single vortex pairing inside a wide domain without the Doppler effect. The strategy was to study the vortex pairing in a bi-dimensional mixing layer under temporal development. The method used was the direct numerical simulation (DNS) of the compressible bidimensional (2D) Navier Stokes equations written in a nonconservative form of the characteristics formulation. The results showed that the vortex modulation did not produce a significant change on the vortex pairing sound.

The major source of aircraft noise at take-off is jet noise. If jet noise is not adequately addressed environmental impact concerns will constrain the planned growth of the air transport system. A considerable amount of research worldwide has therefore been aimed at identifying ways to reduce jet noise including development of a predictive tool that can estimate the noise generated by new nozzle designs. Current noise prediction techniques, however, still require the input of empirically calibrated noise source models and their performance is still inadequate. In addition, development of detailed noise source identification measurements and the associated understanding of how to control (and reduce) the noise at the source has been limited. The fundamental turbulence property which acts as the source of propagating noise in shear layers is the two-point space-time velocity correlation (Rijkl). Very few measurements exist for this property to guide model development. It is therefore the aim of the work reported in this thesis to provide new experimental data that helps identify the turbulence sources located within the shear layer of jets. The technique of Partical Imaging Velocimetry (PIV) is used to capture directly the flowfield and all relevant turbulent statistics.

L'air que nous respirons au travers des voies aériennes supérieures est essentiel pour la vie et pour la communication orale. Dans les études de production de parole humaine, l'écoulement d'air est en général extrêmement simplifié. Or cet écoulement est complexe car turbulent et fortement sensible aux conditions limites. Dans le cas de la production de fricatives non voisées, une description plus fine de l'écoulement s'avère nécessaire pour pouvoir modéliser correctement les mécanismes aéroacoustiques sous-jacents. A l'aide d'expériences in-vitro et de simulations numériques, l'objectif de cette thèse est de contribuer à la modélisation et la caractérisation aéroacoustique d'écoulements dans des configurations de type canal avec obstacle(s), avec application à la production de fricatives non voisées. Une attention toute particulière est portée à l'influence des conditions limites et à la turbulence. / Airflow through the human upper airways is essential for life and for oral communication. In studies dealing with human speech production, airflow is mostly severely simplified. Nevertheless, this airflow is complex owing to turbulence and extreme sensitivity to boundary conditions. Recently, deeper attention has been given to characterize the airflow in the case of unvoiced fricative production and the necessity of obtaining a more detailed flow description has been outlined. With the aid of in-vitro experiments and numerical simulations, the aim of the current PhD research is to contribute to the aeroacoustic modeling and characterization of airflows through various configurations of ducts with obstacle(s), relevant for unvoiced fricative speech production. Special interest is given to the influence of boundary conditions and to turbulence.

Coordenação de Aperfeiçoamento de Pessoal de Nível Superior / The present work refers to the characterization of the sound field generated by subsonic jets in crossflow (JICF). This phenomenon that results from a jet of fluid discharged perpendicularly to a moving medium has a very complex, but well established, fluid dynamics and a sound field yet unexplored. For the complete characterization of this phenomenon, a hybrid methodology of low computational cost that uses a combination of commercial and open source packages is used. The fluid dynamics part is solved by the commercial code CFD ++ by Metacomp Inc. through Reynolds Average Navier-Stokes Equations (RANS), and the noise calculations are performed on an open source code using the Lighthill Ray-Tracing method (LRT). An extensive validation step is performed to demonstrate the ability and highlight the limitations of the methods used for predicting the jet s behavior. This work brings a large contribution to the development of JICF noise research by showing the existence of a region of relative silence in these jets. / O presente trabalho refere-se ao estudo da caracterização do campo acústico de jatos subsônicos submetidos a escoamento cruzado (JSEC). Este fenômeno que resulta de um jato de fluido descarregado perpendicularmente a um meio em movimento, possui uma dinâmica muito complexa, mas bem estabelecida, e um campo acústico ainda inexplorado. Para a completa caracterização deste fenômeno, utiliza-se uma metodologia híbrida de baixo custo computacional, que associa pacotes comerciais e códigos abertos. A parte fluidodinâmica é solucionada pelo código computacional comercial CFD++ da empresa Metacomp Inc. por meio das Equações Médias de Reynolds (RANS), e os cálculos de ruído são realizados em código aberto utilizando o método de Lighthill Ray-Tracing (LRT). Uma extensa etapa de validações é realizada para comprovar a capacidade e evidenciar as limitações dos métodos utilizados na previsão do comportamento do jato. Este trabalho contribui para o avanço das pesquisas na área de ruído de JSEC, tendo identificado a existência de uma região de silêncio nesses jatos. / Mestre em Engenharia Mecânica

Tanto os motores turbo-jato quanto os turbo-fan, são os maiores responsáveis pela geração de ruído durante a decolagem, segmento de subida e de aceleração de uma aeronave. Devido a isto, o problema de ruído em jatos vem sendo intensamente investigado ao longo dos últimos anos. Já na fase do pouso, o slat é uma das fontes de ruído mais importantes. Para este caso, na maioria das aplicações práticas, existe o descolamento da camada limite no intradorso do slat a partir de onde se desenvolve uma camada de mistura. Ainda assim, existem inúmeros aspectos de tais escoamentos que precisam de investigação. Uma abordagem frequentemente feita para o estudo da instabilidade hidrodinâmica e ruído em jatos é o estudo de metade do jato. A estratégia consiste em estudar os fenômenos na camada de mistura, o que é uma aproximação razoável quando o jato tem diâmetro muito grande comparado à espessura da camada cisalhante que se desenvolve nas bordas do jato. Assim, alguns aspectos do ruído gerado pelos modos axi-simétricos de instabilidade são em grande parte reproduzidos. Um aspecto aparentemente jamais estudado antes é o efeito do emparelhamento de vórtices de diferentes geometrias na camada de mistura. Caso o efeito da modulação dos vórtices produzisse um padrão de ruído com características diferentes no emparelhamento, um controle ativo de escoamento por excitação periódica poderia ser usado para reduzir o ruído em jatos. O objetivo do presente trabalho é investigar tal efeito. A idéia é investigar este emparelhamento de vórtices na camada de mistura em desenvolvimento temporal bi-dimensional. Com isto foi possível visualizar um emparelhamento isolado de outros emparelhamentos e sem o efeito Doppler (presente na camada de mistura em desenvolvimento espacial). O método adotado foi a simulação numérica direta (DNS) das equações de Navier Stokes compressíveis na forma não-conservativa escritas na formulação característica. Os resultados mostram que a modulação dos vórtices não produz alteração significativa do ruído gerado no emparelhamento. / Turbo-fan and turbo-jet engines are the most important noise sources during the aircraft take off, climb and acceleration segments. Owing to this fact, the jet flow noise has been studied in the past years. For the landing stage, the slat is an important sound source. In this case, the slat leading edge frequently experiences a boundary layer deattachment causing the development of a mixing layer inside the slot. Nevertheless, there are many aspects of such phenomenon that have not been studied yet. Mixing layers constitutes an usual approach for jet flow instability in aeroacoustics studies. The stategy is to study the mixing layer in order to understand the jet-flow. This strategy becomes better as the ratio between the jet diameter and mixing layer thickness becomes larger. This approach is only reazonable for the jet flow axi-symetric unstable modes. The effect of vortex modulation on the vortex pairing sound production has not been found in the literature. If such effect could cause a significant change in the sound generation patterns, an active flow control system could be developed in order to enhance the jet noise performance. The purpose of the present work was to investigate such effect. It was also possible to observe a single vortex pairing inside a wide domain without the Doppler effect. The strategy was to study the vortex pairing in a bi-dimensional mixing layer under temporal development. The method used was the direct numerical simulation (DNS) of the compressible bidimensional (2D) Navier Stokes equations written in a nonconservative form of the characteristics formulation. The results showed that the vortex modulation did not produce a significant change on the vortex pairing sound.

Depuis plusieurs décennies, le trafic aérien ne cesse de croître. Ainsi, près de 6 milliards de passagers transitent dans le monde par an. Les objectifs européens à l’horizon 2020 en terme d’émission sonore des aéronefs imposent une réduction de 10 dB par point de mesure par rapport aux aéronefs de l’an 2000. Dans ce contexte, le projet européen VALIANT (VALidation and Improvement of Airframe Noise prediction Tools) a pour but principal de tester, valider et améliorer les codes numériques et les modèles de prédiction du bruit de cellule (trains d’atterrissage + voilure) sur des géométries simplifiées afin de disposer de cas tests pour les recherches futures. L’objectif de la thèse, associé à la contribution de l’ECL dans ce projet, est de créer des bases de données expérimentales fiables sur des systèmes à deux éléments – bec/aile et aile/volet – et de modéliser analytiquement le bruit issu de tels systèmes. La thèse s’est concentrée sur un système aile/volet non porteur et parallèle dans un écoulement de soufflerie à veine ouverte, en configuration d’alignement ou de recouvrement partiel, menant à de possibles interactions aérodynamiques et/ou acoustiques. Les mesures ont été faites pour différentes vitesses d’écoulement (30 − 100 m~s), avec une attention particulière à 50 m~s (M0 ∼ 0, 15). Le taux de turbulence de l’écoulement incident est modifiable par l’ajout d’une grille de turbulence à maille large placée dans la section de sortie du convergent. Les résultats aérodynamiques (fil chaud, pression en paroi) ont révélé la présence d’une forte interaction lorsque la distance entre les deux corps est de l’ordre de grandeur de la couche limite turbulente au bord de fuite de l’aile. De plus, le couplage acoustique a lieu lorsque la longueur de recouvrement est positive ou nulle. Des mesures de localisation de sources menées par l’ONERA/DSNA ont permis de valider les mesures de champ lointain en confirmant l’absence de sources de bruit d’installation en dessous de 10 kHz. Par ailleurs, des comparaisons avec les simulations numériques donnent de bons accords. Du point de vue analytique, le problème mathématique de deux plaques planes en recouvrement partiel dans un écoulement uniforme a été posé et une réduction bidimensionnelle a été justifiée. Le problème n’ayant pas de solution exacte, plusieurs modèles issus de la littérature – théories de Howe et d’Amiet – ont été étudiés. Les plus pertinents ont été confrontés aux résultats expérimentaux, révélant les limites asymptotiques de ces modèles. Un modèle original est alors proposé pour la géométrie du problème posé, sans hypothèse restrictive. La démarche est basée sur une procédure de diffraction itérative permettant de prendre en compte la proximité des deux corps et utilisant la fonction de Green exacte du demi-plan en écoulement uniforme. Le modèle prédit des comportements qualitatifs angle/fréquence proches des résultats expérimentaux. La prise en compte de la statistique des rafales incidentes reste néanmoins à effectuer afin de procéder à des comparaisons quantitatives. Une campagne expérimentale complémentaire avec une marche descendante permet de mettre en évidence les écoulements de cavité arrière d’une aile, plus proche de la réalité. De même, des mesures sur une configuration bec/aile a été testée et la prise en compte de la déflexion du jet de la soufflerie pour la réfraction des ondes sonores par la couche de cisaillement a été proposée. / Air traffic still grows from decades, with yearly 6 billion passengers nowadays in the world. By 2020, the EC imposes aircraft noise reductions by 10 dB per measuring point with respect to the status in 2000. In this context, VALIANT (VALidation and Improvement of Airframe Noise prediction Tools) is an EC-supported project that aims at testing, validating and improving numerical codes and analytical/theoretical models for the prediction of airframe noise (landing gears + high-lift devices) in simplified configurations in order to generate test cases for research needs. The main objective of the thesis in connection with ECL contribution in the scope of VALIANT project is to generate reliable experimental databases for 2-element systems – slatwing and wing-flap – as well as to analytically model overlapping configurations. It is particulary focussed on the experimental and analytical studies of a non lifting wing-flap system in a parallel flow, in aligned and overlapping arrangements. This is aimed at discussing likely aerodynamic and/or acoustic interactions. The tests have been carried out in an open-jet anechoic wind-tunnel for each arrangement and for several flow speeds (30-100 m/s), with main interest on 50 m/s (M0 ∼ 0, 15). The turbulence rate could be changed by fixing a removable turbulence grid with a large mesh at the outlet cross-section of the duct. Aerodynamic results (hot-wire anemometry, wall-pressure) show a strong interaction when the wing-flap distance is about the wing trailingedge boundary layer thickness. Acoustic coupling can be pointed out in cases of overlap. Source localization tests performed by ONERA/DSNA have permitted to validate far-field acoustic tests since no installation effect source seems to strongly radiate below 10 kHz. A good agreement with numerical simulations has been shown for every test. In order to predict noise analytically for a 2-element system in case of overlap in a uniform flow, the mathematical statement has been defined and a 2D-reduction of the equation system can be justified. Since no exact solution exists, several models from the literature – Howe’s and Amiet’s theories – have been studied. Comparisons between overlapping half-planes and slotted trailing-edge models proposed by Howe and experimental results show obvious limitations in the predictions. Then, an original model is proposed involving two bodies in close overlap arrangement, with no assumption. It is based on an iterative scattering procedure to take into account the close vicinity of the two bodies, using the exact half-plane Green’s function in a uniform flow. Convergence is relatively quick and qualitative predictions in angle/frequency behaviour show a good agreement with experiments. However, the statistics of the vortical flows responsible for the sound must be implemented for better comparisons. Other experiments have been done with a backward-facing step – it represents wing trailing-edge cove – to make cavity flow mechanisms appear, such as what is observed in real HLD. Finally, a series of tests has been performed involving a slat-wing system and an angular correction due to refraction of sound waves in shear-layer for a deflected jet has been proposed.

Résumé : La réduction du bruit tonal des ventilateurs basse vitesse est un défi très important pour l’industrie. Lorsqu’il émerge du bruit large bande, ce rayonnement est la source de gênes auprès de la population, que ce soit pour de petits ventilateurs d’ordinateurs ou de gros ventilateur miniers. Afin de contrôler le bruit tonal, de nombreuses techniques ont été développées au fil de ces dernières décennies. Une méthode alliant simplicité et efficacité se démarque néanmoins : le contrôle par obstruction de l’écoulement. Malgré les études menées jusqu’alors, les mécanismes aéroacoustiques de réduction du bruit associés à cette méthode restent mal compris. Pour répondre à cette problématique, ce projet de Doctorat s’intéresse à l’étude de l’intéraction entre l’obstruction et le ventilateur au moyen de simulations aéro-acoustiques. De plus, une méthodologie numérique de design de l’obstruction est proposée afin de réduire les coûts associés aux multiples test expérimentaux. / Abstract : Tonal noise radiated by low-speed fans is a prime challenge for many industries. When this component emerges from the broadband noise, the acoustic radiation is particularly harsh for the human ear, whether it comes from a small computer cooling fan or from a large mine ventilation fan. Several methods have been developed over the last decades to control tonal noise. Nevertheless, one simple and efficient technique stands out: the adaptive passive control with flow obstruction. Despite all the research conducted on this method, the aeroacoustic mechanisms responsible for the noise reduction are not fully understood. Therefore, the present thesis aims at investing the obstruction-fan interaction using aeroacoustic simulations. Moreover, a numerical design methodology is proposed to reduce the cost induced by extensive experimental tests.