Com o desenvolvimento para aeronaves de propulsores turbo-fan com elevada razão de derivação, componentes da estrutura do avião passaram a ter relevância na geração de ruído aerodinâmico, principalmente durante a aproximação e o pouso. Dentre esses componentes, o eslate se destaca por ser uma fonte que se estende ao longo de praticamente toda a envergadura da asa. Neste trabalho, simulações numéricas foram feitas no intuito de considerar configurações práticas nas análises do ruído aeroacústico gerado pelo eslate. Um código comercial baseado no Método Lattice-Boltzmann foi usado no cálculo do escoamento transiente em torno do aerofólio MD30P30N. O domínio computacional simulado imitou a configuração geométrica de um túnel de vento. Foi levado em consideração o efeito da presença de duas formas de excrescência que são comuns na cova do eslate de aeronaves comerciais. Uma delas foi um selo que fica posicionado na parede da cova e a outra, um tubo do sistema anti-gelo. Tanto o escoamento transiente na região da cova quanto as características do ruído aeroacústico propagado para o campo distante foram analisados. Uma metodologia que impõe condição de parede com escorregamento livre no es- late e elemento principal, permitindo assim uma redução do custo computacional, foi usada. A abordagem foi ainda testada para a condição de um aerofólio submetido a escoamento cruzado, simulando uma asa infinita com enflechamento. Também uma modificação na metodologia, para que ela possa ser empregada em aerofólios com elevados ângulos de ataque, foi proposta e testada. O código híbrido MSES foi usado para o cálculo da espessura de deslocamento na camada limite do aerofólio. A modificação na geometria baseada em \'delta\'* causou uma melhora da solução aeroacústica de uma simulação empregando paredes com escorregamento livre, tomando como base de comparação a solução com paredes sem escorregamento. Simulações com selo dentro da cova, perto do recolamento, mostraram que, em certas circunstâncias, há um bloqueio dos vórtices da camada de mistura, intensificando picos tonais no espectro do ruído. A variação da posição do selo mostrou um efeito significativo no ruído do eslate, de forma que um selo suficientemente afastado do recolamento modificou o espectro do ruído do eslate. Os resultados com o aerofólio enflechado indicam que, também neste caso, o ruído do eslate não depende diretamente da camada limite na cúspide, mas da circulação do aerofólio. Por sua vez, a presença do tubo na cova aumenta significativamente a intensidade do ruído de banda larga produzido pelo eslate. Em uma asa sem enflechamento, o tubo causa também um aumento substancial na intensidade de picos tonais de baixa frequência. / The development of high by-pass ratio turbo-fan engine turned the airframe noise into an important component in a commercial airplanes\' noise characteristics. Between the airframe noise sources the slat can be highlighted as it extends almost along the whole wing span. Numerical simulation was carried out in order to consider practical configuration in the aeroacoutic noise generated by the slat. The effects of two different excrescences, which are normally present in commercial airplanes\' slat cove, were taken into account. One of them was a seal attached to the cove wall and the outher one was a tube that compose the anti-icing system. Both unsteady flow in cove region and far-field noise characteristics were analysed. A methodology that impose free-slip wall boundary condition on slat and main element surfaces was employed, which allowed the reduction of computational requirements. This approach was also tested for airfoil with crossflow, which simulates an infinite swept wing. Also a modification of the methodology was proposed and tested to extend its application in high-lift airfoils under higher angle of attack. A commercial code based on the Lattice-Boltzmann Method was used to compute the unsteady flow over the MD30P30N airfoil. The simulated computational domain imitates the geometry of a wind tunnel. The hybrid Euler/IBL code MSES was employed to calculate the displacement thickness of the airfoil\'s boundary layers. The geometry modification based on \'delta\'* caused a improvement on the aeroacoustic solution of a free-slip simulation, the no-slip simulation results being taken as reference. Simulations of geometries with relatively small seal close to the reattachment point showed that a blockage of the mixing layer vortices hapens and tonal peaks are intensified in the far-field noise spectrum. The variation of the seal position showed a significant effect on the slat noise, so that a seal farther from the reattachment modified affected both the shape and intensity of the noise spectrum. Results with the swept airfoil indicates that, even in the presence of crossflow, the slat noise does not depend on the cusp boundary layer, namely it is more sensitive to the airfoil circulation. The tube crossing the slat cove augmented significantly the broadband noise generated by the slat. In an unswept wing it also caused a substantial increase in the low-frequency tonal peaks.

Com o desenvolvimento para aeronaves de propulsores turbo-fan com elevada razão de derivação, componentes da estrutura do avião passaram a ter relevância na geração de ruído aerodinâmico, principalmente durante a aproximação e o pouso. Dentre esses componentes, o eslate se destaca por ser uma fonte que se estende ao longo de praticamente toda a envergadura da asa. Neste trabalho, simulações numéricas foram feitas no intuito de considerar configurações práticas nas análises do ruído aeroacústico gerado pelo eslate. Um código comercial baseado no Método Lattice-Boltzmann foi usado no cálculo do escoamento transiente em torno do aerofólio MD30P30N. O domínio computacional simulado imitou a configuração geométrica de um túnel de vento. Foi levado em consideração o efeito da presença de duas formas de excrescência que são comuns na cova do eslate de aeronaves comerciais. Uma delas foi um selo que fica posicionado na parede da cova e a outra, um tubo do sistema anti-gelo. Tanto o escoamento transiente na região da cova quanto as características do ruído aeroacústico propagado para o campo distante foram analisados. Uma metodologia que impõe condição de parede com escorregamento livre no es- late e elemento principal, permitindo assim uma redução do custo computacional, foi usada. A abordagem foi ainda testada para a condição de um aerofólio submetido a escoamento cruzado, simulando uma asa infinita com enflechamento. Também uma modificação na metodologia, para que ela possa ser empregada em aerofólios com elevados ângulos de ataque, foi proposta e testada. O código híbrido MSES foi usado para o cálculo da espessura de deslocamento na camada limite do aerofólio. A modificação na geometria baseada em \'delta\'* causou uma melhora da solução aeroacústica de uma simulação empregando paredes com escorregamento livre, tomando como base de comparação a solução com paredes sem escorregamento. Simulações com selo dentro da cova, perto do recolamento, mostraram que, em certas circunstâncias, há um bloqueio dos vórtices da camada de mistura, intensificando picos tonais no espectro do ruído. A variação da posição do selo mostrou um efeito significativo no ruído do eslate, de forma que um selo suficientemente afastado do recolamento modificou o espectro do ruído do eslate. Os resultados com o aerofólio enflechado indicam que, também neste caso, o ruído do eslate não depende diretamente da camada limite na cúspide, mas da circulação do aerofólio. Por sua vez, a presença do tubo na cova aumenta significativamente a intensidade do ruído de banda larga produzido pelo eslate. Em uma asa sem enflechamento, o tubo causa também um aumento substancial na intensidade de picos tonais de baixa frequência. / The development of high by-pass ratio turbo-fan engine turned the airframe noise into an important component in a commercial airplanes\' noise characteristics. Between the airframe noise sources the slat can be highlighted as it extends almost along the whole wing span. Numerical simulation was carried out in order to consider practical configuration in the aeroacoutic noise generated by the slat. The effects of two different excrescences, which are normally present in commercial airplanes\' slat cove, were taken into account. One of them was a seal attached to the cove wall and the outher one was a tube that compose the anti-icing system. Both unsteady flow in cove region and far-field noise characteristics were analysed. A methodology that impose free-slip wall boundary condition on slat and main element surfaces was employed, which allowed the reduction of computational requirements. This approach was also tested for airfoil with crossflow, which simulates an infinite swept wing. Also a modification of the methodology was proposed and tested to extend its application in high-lift airfoils under higher angle of attack. A commercial code based on the Lattice-Boltzmann Method was used to compute the unsteady flow over the MD30P30N airfoil. The simulated computational domain imitates the geometry of a wind tunnel. The hybrid Euler/IBL code MSES was employed to calculate the displacement thickness of the airfoil\'s boundary layers. The geometry modification based on \'delta\'* caused a improvement on the aeroacoustic solution of a free-slip simulation, the no-slip simulation results being taken as reference. Simulations of geometries with relatively small seal close to the reattachment point showed that a blockage of the mixing layer vortices hapens and tonal peaks are intensified in the far-field noise spectrum. The variation of the seal position showed a significant effect on the slat noise, so that a seal farther from the reattachment modified affected both the shape and intensity of the noise spectrum. Results with the swept airfoil indicates that, even in the presence of crossflow, the slat noise does not depend on the cusp boundary layer, namely it is more sensitive to the airfoil circulation. The tube crossing the slat cove augmented significantly the broadband noise generated by the slat. In an unswept wing it also caused a substantial increase in the low-frequency tonal peaks.

As improving the performance of turbofan designs becomes increasingly difficult, manufacturers are looking to new technologies for the next generation of jet engines. An 'open rotor' replaces the fan of the turbofan with a set of external rotors. This has the potential to offer a significant improvement in propulsive efficiency, but the design for low noise is a key challenge. Hence, high fidelity noise prediction methods are needed to accurately predict and compare the noise of different designs. This thesis focuses on one set of methods based on the Ffowcs Williams-Hawkings (\fwh) equation. This equation is considered to be the most realistic description of aeroacoustic noise generation, as it is a direct rearrangement of the Navier-Stokes equations. The \fwh\ equation is difficult to solve for realistic test cases such as an open rotor, and is susceptible to several types of error. This thesis categorises these errors as ``input'', ``neglection'' and ``discretisation'' errors. Discretisation errors arise from the need to integrate a discretised source field for the total noise, neglection errors result from needing to ignore part of the source field for practical reasons, and input errors relate to any errors caused by inaccurate input to the solver. The fundamental motivation of this thesis is to advance the understanding of neglection and discretisation errors and how they can be mitigated, in order to develop best practice solvers and methodologies for application to open rotors. Dimensional analysis is combined with analytical flow solutions to develop a process for isolating and quantifying discretisation errors. This process is used to study a wide range of solver methodologies and select a best practice solver methodology for open rotor noise prediction. This first-of-a-kind study produces a solver methodology that reduces discretisation errors by an order of magnitude compared to an industry standard solver. Previous research into neglection errors has shown that avoiding density perturbations in acoustic source terms can be beneficial. This thesis uses a generic aeroacoustic analogy to provide a new, physically intuitive method of incorporating a surface discontinuity that enables density perturbations to be avoided in a far more elegant manner than previous research. The above method improvements are investigated using a modern open rotor rig test case. The results demonstrate that discretisation and neglection errors can be severe in realistic cases and the potential of the method improvements to significantly mitigate them.

In a society where environmental noise is becoming a major health and economical concern, sound emissions are an increasingly critical design factor for vehicle manufacturers. With about a quarter of the European population living close to roads with heavy traffic, traffic noise in urban landscapes has to be addressed first. The current introduction of electric vehicles on the market and the need for sound systems to alert their presence is causing a shift in mentalities requiring engineering methods that will have to treat noise management problems from a broader perspective. That in which noise emissions need not only be considered as a by-product of the design but as an integrated part of it. Developing more sustainable ground transportation will require a better understanding of the sound field emitted in various realistic operating conditions, beyond the current requirements set by the standard pass-by test, which is performed in a free-field. A key aspect to improve this understanding is the development of efficient numerical tools to predict the generation and propagation of sound from moving vehicles. In the present thesis, a methodology is proposed aimed at evaluating the pass-by sound field generated by vehicle acoustic sources in a simplified urban environment, with a focus on flow sound sources. Although it can be argued that the aerodynamic noise is still a minor component of the total emitted noise in urban driving conditions, this share will certainly increase in the near future with the introduction of quiet electric engines and more noise-efficient tyres on the market. This work presents a complete modelling of the problem from sound generation to sound propagation and pass-by analysis in three steps. Firstly, computation of the flow around the geometry of interest; secondly, extraction of the sound sources generated by the flow, and thirdly, propagation of the sound generated by the moving sources to observers including reflections and scattering by nearby surfaces. In the first step, the flow is solved using compressible detached-eddy simulations. The identification of the sound sources in the second step is performed using direct numerical beamforming with linear programming deconvolution, with the phased array pressure data being extracted from the flow simulations. The outcome of this step is a set of uncorrelated monopole sources. Step three uses this set as input to a propagation method based on a point-to-point moving source Green's function and a modified Kirchhoff integral under the Kirchhoff approximation to compute reflections on built surfaces. The methodology is demonstrated on the example of the aeroacoustic noise generated by a NACA air inlet moving in a simplified urban setting. Using this methodology gives insights on the sound generating mechanisms, on the source characteristics and on the sound field generated by the sources when moving in a simplified urban environment. / I ett samhälle där buller håller på att bli ett stort hälsoproblem och en ekonomisk belastning, är ljudutsläpp en allt viktigare aspekt för fordonstillverkare. Då ungefär en fjärdedel av den europeiska befolkningen bor nära vägar med tung trafik, är åtgärder för minskat trafikbuller i stadsmiljö en hög prioritet. Introduktionen av elfordon på marknaden och behovet av ljudsystem för att varna omgivningen kräver också ett nytt synsätt och tekniska angreppssätt som behandlar bullerproblemen ur ett bredare perspektiv. Buller bör inte längre betraktas som en biprodukt av konstruktionen, utan som en integrerad del av den. Att utveckla mer hållbara marktransporter kommer att kräva en bättre förståelse av det utstrålade ljudfältet vid olika realistiska driftsförhållanden, utöver de nuvarande standardiserade kraven för förbifartstest som utförs i ett fritt fält. En viktig aspekt för att förbättra denna förståelse är utvecklingen av effektiva numeriska verktyg för att beräkna ljudalstring och ljudutbredning från fordon i rörelse. I denna avhandling föreslås en metodik som syftar till att utvärdera förbifartsljud som alstras av fordons akustiska källor i en förenklad stadsmiljö, här med fokus på strömningsgenererat ljud. Även om det aerodynamiska bullret är fortfarande en liten del av de totala bullret från vägfordon i urbana miljöer, kommer denna andel säkerligen att öka inom en snar framtid med införandet av tysta elektriska motorer och de bullerreducerande däck som introduceras på marknaden. I detta arbete presenteras en komplett modellering av problemet från ljudalstring till ljudutbredning och förbifartsanalys i tre steg. Utgångspunkten är beräkningar av strömningen kring geometrin av intresse; det andra steget är identifiering av ljudkällorna som genereras av strömningen, och det tredje steget rör ljudutbredning från rörliga källor till observatörer, inklusive effekten av reflektioner och spridning från närliggande ytor. I det första steget löses flödet genom detached-eddy simulation (DES) för kompressibel strömning. Identifiering av ljudkällor i det andra steget görs med direkt numerisk lobformning med avfaltning med hjälp av linjärprogrammering, där källdata extraheras från flödessimuleringarna. Resultatet av detta steg är en uppsättning av okorrelerade akustiska monopolkällor. Steg tre utnyttjar dessa källor som indata till en ljudutbredningsmodel baserad på beräkningar punkt-till-punkt med Greensfunktioner för rörliga källor, och med en modifierad Kirchhoff-integral under Kirchhoffapproximationen för att beräkna reflektioner mot byggda ytor. Metodiken demonstreras med exemplet med det aeroakustiska ljud som genereras av ett NACA-luftintag som rör sig i en förenklad urban miljö. Med hjälp av denna metod kan man få insikter om ljudalstringsmekanismer, om källegenskaper och om ljudfältet som genereras av källor när de rör sig i en förenklad stadsmiljö. / <p>QC 20170425</p>

The work deals with the use of geometric parameterization for shape description of some parts of the airplane. Geometric parametrization is used for creating a parametric model airfoil. This parametric model allows local deformations pobrchu profile and can easily be applied to generate the geometry of the wing or other parts letoumu. Some properties of the parametric model were tested applications in aerodynamic optimization. Furthermore, the work deals with the parametric description of the blades, the aerodynamic optimization and noise analysis. For propeller blade were created distribution function of the control parameters that can be used in aerodynamic optimization of the blades. Geometric parameterization is used for identifying the location and other characteristics of noise sources.