The fow around bluff bodies is an essential topic in fuid dynamics. This fow is characterized by large vortical fow regions separating from the surface of the bluff body, and they cause oscillating drag and lift forces on the structure. The fow around an infinite long cylinder is a well-known case being studied in the literature. However, a cylinder with low aspect-ratio piercing the free surface has not been studied much although such an arrangement can be found in many floating offshore structures. In this thesis the results of CFD calculations are presented for a fixed, free surface piercing cylinder with an aspect-ratio L/D equals to 2. The Reynolds number was equal to 4:3 x 104 indicating that the flow is in the sub-critical turbulent regime. An extensive methodology of verication and validation is followed to investigate the reliability of the results. To investigate the effect of the free surface on the calculated hydrodynamic loads, two approaches have been considered: a double-body symmetry condition and an interface capturing Volume-of-Fluid (VoF) method. Additionally, two turbulence models are investigated: a two-equation turbulence model; a non-linear Explicit Algebraic Reynolds Stress Model (EARSM); and the Improved Delayed Detached Eddy Simulation (IDDES) turbulence model. The results are presented in terms of integral results (drag and lift coefficients) and flow visualizations. Based on the results of the cases in which the free surface was modeled as a double body symmetry boundary condition, it is concluded that the model is not suitable for this type of flow as the model damps out the flow dynamics due to over-production of eddy-viscosity. Hence, the characteristic oscillating lift forces are not captured using this turbulence model. However, this turbulence model showed good agreements regarding the flow fields in comparison with experimental PIV measurements. Results of the case modeled with EARSM turbulence model shows better agreement with the experimental results compared with the turbulence model. In the cases where the free-surface is considered, results with the EARSM turbulence model show similar results for the drag forces whereas the lift uctuations were one order of magnitude smaller, compared with the double body case. Lastly, the results using the IDDES turbulence model and free-surface VoF modeling are shown to produce the best comparison with the experimental results, regarding both, integral values and flow field results. / O escoamento ao redor de corpos rombudos é um tópico essencial na dinâmica de fluidos. O escoamento é caracterizado por regiões com grande vorticidade que se separam do corpo e causam oscilações das forças de arrasto e sustentação sobre a estrutura. O escoamento ao redor de cilindros longos é um tema que tem sido extensivamente estudado com muitos trabalhos encontrados na literatura. Entretanto, o cilindro com baixa razão de aspecto perfurante à superfície livre é um caso pouco estudado, apesar desta estrutura ser encontrada em várias estruturas oceânicas flutuantes. Esta dissertação apresenta cálculos numéricos para o escoamento ao redor de um cilindro fixo, que trespassa a superfície livre com razão de aspecto L/D igual a 2. O problema é estudado em um regime subcrítico de turbulência, com número de Reynolds igual a 4:3 x 104. Uma vasta metodologia de verificação e validação foi seguida para avaliar a confiabilidade dos resultados obtidos numericamente. Para investigar os efeitos da superfície livre nas cargas hidrodinâmicas, duas abordagens s~ao consideradas: condição de simetria de duplo corpo e um método de captura de interface Volume of Fluid. Além disso, dois modelos de turbulência foram investigados: o modelo não linear Explicit Algebraic Reynolds Stress Model (EARSM), e o modelo de turbulência Improved Delayed Detached Eddy Simulation (IDDES). Os resultados relacionados aos coeficientes de arrasto e sustentação são apresentados a partir de análise estatística, complementados através de ilustrações que permitem visualizar os campos de escoamento e pressão. Com base nos resultados de casos em que a superfície livre é modelada com uma condição de contorno de simetria, conclui-se que o modelo de turbulência não é adequado para este tipo de escoamento, pois o modelo amortece a dinâmica do escoamento devido à superprodução de viscosidade turbulenta. Consequentemente, as oscilações na força de sustentação não são capturadas usando este modelo. Entretanto, resultados dos campos médios do escoamento mostram-se concordantes com imagens experimentais obtidas com técnicas de PIV - Particle Image Velocimetry. Resultados do caso modelado com o modelo de turbulência EARSM mostram melhores concordâncias na comparação dos parâmetros estatísticos com experimentos do que o modelado com o modelo EARSM. Nos casos em que a superfície livre é modelada com o método VoF, o modelo de turbulência EARSM mostra resultados semelhantes para o arrasto, enquanto as flutuações da sustentação apresentam-se uma ordem de grandeza menores, quando comparadas ao caso de duplo corpo. Resultados usando o modelo de turbulência IDDES e VoF apresentam melhores comparações aos resultados experimentais, tanto para os parâmetros estatísticos quando para as visualizações do escoamento.

The goal of this project is to use inspiration acquired from bird flight to optimize the wing planform of micro-air vehicle wings. Micro-air vehicles are used by the military for surveillance and for search and rescue missions by civilian first-responders. These vehicles fly in the same low Reynolds number regime as birds, and have low aspect ratios similar to the pheasants and grouse of the order Galliformes. Conventional analysis is difficult for low Reynolds numbers, prompting use of biologically inspired methods of optimization. Genetic algorithms, which mimic the process of evolution in nature, were used to define wing shapes that were tested in wind tunnel experiments. In these experiments, lift-drag ratios at various angles of attack were measured on scale model micro-air vehicle wings (with variable length feathers) similar in shape to a bird wing. The planform shape of the scale model wing evolved in the wind tunnel flow over successive generations to ultimately produce superior wings with higher lift-drag ratios. The low angle of attack wings were easily optimized into a wing shape different from and potentially more efficient than the oft-used Zimmerman planform. The process was repeated for a higher angle of attack, near stall conditions, which yielded a different wing planform shape. Chord distributions of the optimized low angle of attack wings were found to closely match the same distributions of birds from the order Galliformes. Results from flow visualization studies meant to illuminate possible physics responsible for the higher lift-drag ratios were also investigated.

The effects of shape and relative submergence (the ratio of flow depth to obstacle height, d/H) were investigated on the wakes around four different low-aspect-ratio wall-mounted obstacles: semi-ellipsoids with the major axes of the base ellipses aligned in the streamwise and transverse directions, two cylinders with aspect ratios matching the ellipsoids. Wake structure of a fully submerged, spherical obstacle was also investigated in the same flow conditions to provide insight into the flow obstacle interaction with ramification to sediment transport. A low-aspect-ratio semi-ellipsoid was chosen as broad representative of a freshwater mussel projecting from a river bed, and a sphere was employed as representative of a boulder. Two cylinders were used due to their similarity to geometries investigated in other studies. Digital Particle Image Velocimetry and thermal anemometry were used to interrogate the flow. For ellipsoids and cylinders, streamwise features observed in the mean wake included counter-rotating distributions of vorticity inducing downwash (tip structures), upwash (base structures), and horseshoe vortices. In particular, the relatively subtle change in geometry produced by the rotation of the ellipsoid from the streamwise to the transverse orientation resulted in a striking modification of the mean streamwise vorticity distribution in the wake. Tip structures were dominant in the former case while base structures were dominant in the latter. A vortex skeleton model of the wake is proposed in which arch vortex structures, shed from the obstacle, are deformed by the competing mechanisms of Biot-Savart self-induction and the external shear flow. An inverse relationship was observed between the relative submergence and the strength of the base structures for the ellipsoids, with a dominant base structure observed for d/H = 1 in both cases. The wake of the sphere is more complex than ellipsoidal geometries. Streamwise features observed in the mean wake including tip, horseshoe structures, and weak upwash. The shedding characteristics and dynamics of the wake were examined. Weak symmetric shedding was observed in the wakes of streamwise and transverse ellipsoids at d/H = 3.9 while cross-spectral measurements confirmed downstream and upstream tilting of arch structures shed by the transverse and streamwise ellipsoids, respectively. Much weaker peaks in the power spectrum were observed for low- and high-aspect-ratio cylinders. While the dominant Strouhal number remained constant as the relative submergence was reduced to d/H = 2.5 for the ellipsoids, it increased abruptly at d/H = 1 and transitioned to an antisymmetric mode. For sphere geometry at d/H = 3.9, a weak dominant frequency was observed close to obstacle junction and the cross-correlation function for symmetric measurements in the wake indicates symmetric shedding. These results demonstrate a means by which to achieve significant modifications to flow structure and transport mechanisms in the flow.

This study demonstrates the applicability of using a modified application strategy of panel method to analyze low aspect ratio wings at preliminary design phases. Conventional panel methods fail to capture the leading edge vortex (LEV) that is shed by wings with low aspect ratios, typically below 2 depending on planform. This aerodynamic phenomenon contributes to a significant amount of the lift of these wings and the result is a drastic underestimation of the lift characteristics when analyzed by conventional panel method. To capture the effect of the leading edge vortex, a panel method code was used with an extended definition of the Kutta condition along portions of the leading edge inducing a vortex to shed from the leading edge and flow aft just inside the leading edge. To validate that this method, it was applied to 2 elliptical planforms with constant thickness where experimental force balance data was available. Additionally, the same 2 wings were analyzed using a finite volume solver to compare pressure distributions and to demonstrate the difference in magnitude of solution times. For comparison purposes, the resulting forces and moments from both computational methods and experimental testing were plotted over a range of angles of attack. Overall, the results demonstrate that a modified panel method could be used during the preliminary design phases for low aspect ratio wings. The panel method can reasonably model the lift and induced drag characteristics of low aspect ratio wings. This method loses applicability beyond the stall point where the leading edge vortex breaks down and oversimplifies pitching moment relation to angle of attack. Additionally, when compared to finite volume solutions of the same scenario, the panel method provided a result 20 to 30 times faster than the finite volume solutions. With this in mind, the modified panel method application strategy lends itself to preliminary design phases of low aspect ratio wings where the level of detail does not warrant finite volume analysis and solution speed has higher priority.

Flow separation is a source of aerodynamic in-efficiency; however by using vortex generators the issue of flow separation can be controlled. This is of particular benefit to flows around bluff bodies which are susceptible to large scale separated flows, such as bodies in ground effect. Previous studies concerning heat transfer applications focused on the ability of low aspect ratio spherical wells (dimples) to produce vortices for flow mixing. Dimpled surfacing on an inverted Tyrrell026 airfoil in ground effect (indicative of high performance automotive aerodynamic applications e.g. Formula One) has been investigated for similar vortex enhanced wake reductions. Experimental measurements using Laser Doppler Anemometry (LDA) and Particle Image Velocimetry (PIV) were taken inside a dimple to provide validation and verification of numerical analyses of dimple flows. The k-ω SST turbulence model showed good agreement to the experimental measurements. Additionally experiments were conducted using LDA and PIV with various configurations of dimple arrays placed from a fixed separation point of a 16˚ rearward facing ramp to determine how the array configuration influenced the large scale separation. The airfoil wake with numerous dimple configurations and placements were measured using LDA. Results showed that an array of dimples with close dimple to dimple spacing there was flow recovery in the airfoil wake from the velocity deficit with no dimples of u/Uo,min=-0.1, to u/Uo,min=0.4 with a dimple array, (at α=10˚, ground clearance h/c=0.313). At α=10˚ reductions in the wake size of 30%, 33%, 58% and 68% were found for the ground clearances of h/c=0.112, 0.134, 0.224 and 0.313 respectively. For numerous dimple array configurations, closely spaced dimple arrays were more effective in reducing the wake size, turbulence intensity and Reynolds stresses than those where dimple spacing was further apart. The chord wise location of the array on the wing affected the angle of incidence of the wing for which the wake was able to be reduced. Arrays placed towards the trailing edge improved wake losses at lower angles of incidence. Dimples placed further forward yielded the most improvement at higher angles of incidence, in part due to the increased venturi effect under the wing.

O desenvolvimento da indústria offshore fez com que a demanda por unidades flutuantes para operações em águas ultraprofundas aumentasse e, com isso, surgiu um maior interesse nos fenômenos decorrentes de vibrações induzidas pelo escoamento em plataformas do tipo spar, TLP e semissubmersível, além de torres para produção de energia eólica (instaladas no mar). Para ampliar o conhecimento nesta área, experimentos foram realizados com cilindros flutuantes com baixa razão de aspecto (L/D = 2) e com diferentes geometrias na extremidade livre . Experimentos com a vibração induzida pelo escoamento em cilindros de seção quadrada e cilindros de seção quadrada e arestas arredondadas com baixa razão de aspecto foram realizados em um tanque de reboque. Estas diferentes geometrias de cilindros foram testadas e suportadas elasticamente por um conjunto de molas lineares. Dois ângulos de incidência diferentes foram testados: 0 e 45 graus. Os resultados de amplitude na direção transversal para modelos submetidos à incidência de 0 graus mostraram ser maiores. Além disso, as oscilações em yaw se mostraram importantes em todos os caso analisados. O efeito das arestas se mostrou importante, particularmente na incidência de 45 graus, para velocidades reduzidas maiores que 8. / The development of the offshore industry has meant that the demand for ultradeep water floating units has increased, and with this, a greater interest in the phenomena arising from FIV in spar, TLP and semi-submersible platforms has arisen. In order to increase the area knowledge, experiments were performed with floating cylinders with different geometries, with low aspect ratio (L/D = 2). Experiments of flow-induced vibration in cylinders with sharp aokokoknd rounded square section with low aspect ratio were performed in a towing tank. These geometries have been tested and elastically supported by a set of linear springs to provide low structural damping to the system. Two different incidence angles were tested: 0 and 45 degrees. The transverse response amplitudes for the 0-degree flow incidence were found to be larger. Moreover, yaw oscillations are important for all the cases analyzed. The rounded effect on the cylinders of square section were important, particularly for the the 45-degree incidence at reduced velocities higher than 8.

The aerodynamic performance of low aspect ratio wings at low Reynolds numbers applicable to micro air vehicle design was studied in this thesis. There is an overall lack of data for this low Reynolds number range, particularly concerning details of local flow behavior along the span. Experiments were conducted to measure the local pressure distributions on a wing at various spanwise locations in a Reynolds number range 30000 < Re < 90000. The model wing consisted of numerous wing sections and had a rectangular planform with NACA0012 airfoil shape with aspect ratio of one. One wing section, with pressure ports at various chordwise locations, was placed at different spanwise locations on a wing to effectively obtain the local pressure information. Integration of the pressure distributions yielded the local lift coefficients. Comparison of the local lift distributions to optimal elliptic lift distribution was conducted. This comparison showed a sharply peaked lift distribution near the wing tip resulting in a drastic deviation from the equivalent elliptic lift distributions predicted by the finite wing theory. The local lift distributions were further analyzed to determine the total lift coefficients vs angle of attack curves, span efficiency factors and the induced drag coefficients. Measured span efficiency factors, which were lower than predictions of the elliptic wing theory, can be understood by studying deviations of measured lift from the elliptic lift distribution. We conclude that elliptic wing theory is not sufficient to predict these aerodynamic performance parameters. Overall, these local measurements provided a better understanding of the low Reynolds number aerodynamics of the low aspect ratio wings.

O aumento das ocorrências de VIM em plataformas flutuantes do tipo \"spar\" e monocoluna serviu de motivação para a investigação dos fundamentos do fenômeno de VIV em cilindros com baixa razão de aspecto e pequena razão de massa. Tal investigação também foi motivada pela necessidade de se preencher lacunas de conhecimento a respeito deste assunto, articularmente por conta da escassa disponibilidade de resultados acerca do VIV em cilindros curtos, bem como pela ausência de modelo fluido que justifique os comportamentos dinâmicos conhecidos. Para o entendimento pretendido, três grupos de experimentos com cilindros dotados de razão de aspecto na faixa 0,1 <= L/D <= 2,0 foram realizados em um canal de água circulante na Escola Politécnica da Universidade de São Paulo, sendo: o primeiro grupo focado nos cilindros curtos estacionários; o segundo nos cilindros curtos de baixa razão de massa, 1,00 <= m* <= 4,36, e dois graus de liberdade; e o grupo final interessado no VIV em cilindros flutuantes, ou seja, razão de massa unitária e seis graus de liberdade. De uma maneira geral, a partir dos resultados aqui obtidos e das comparações com os resultados respectivamente encontrados na literatura, conclui-se que o VIV em cilindros curtos somente acontece se L/D > 0,2. Além de original, a determinação deste valor crítico também identificou outras três regiões com comportamentos fluido-dinâmicos distintos, cada qual marcada por especificidades quanto aos impactos nas amplitudes, frequências e coeficientes de força. Assim sendo, para cilindros com L/D > 2,0 a esteira de von Kármán foi a principal responsável pelas forças sustentação; fato não identificado para os cilindros com 0,5 < L/D < 2,0, onde esta mesma esteira sofreu forte contaminação das estruturas partindo da extremidade livre, principalmente aquelas com vorticidade predominante no plano vertical. Para os cilindros na faixa de 0,2 < L/D <= 0,5, apenas estas últimas estruturas foram responsáveis pelas oscilações de VIV. Finalmente, buscando compreender a origem das forças oscilatórias em cilindros com baixíssima razão de aspecto, \"end-plates\" foram aplicadas e confirmaram que o fenômeno de VIV nestes casos está relacionado à liberação de vórtices junto à extremidade livre, o que indica uma solução interessante para a mitigação do VIM de plataformas. / The increase of VIM occurrences on spar and monocolumn platforms was the motivation to study the vortex-induced vibrations of cylinders with low aspect ratio and small mass ratio under a fundamental perspective. The present work was also motivated by the small number of works in the literature dealing with VIV of cylinders with low aspect ratio, as well as by the scarce concerns about the flow models around this cylinders, which justify the dynamic behaviors observed. Aiming to better understand this problem, three groups of experiments with cylinders of 0.1 <= L/D <= 2.0 were carried out in a recirculating water channel at Escola Politécnica of University of São Paulo, as follow: firstly, the flow around stationary cylinders; secondly, VIV of cylinders with two degrees-of-freedom and 1.00 <= m* <= 4.36. finally, VIV of floating cylinder, thus six degrees-of-freedom. The works concluded that VIV occurs only for cylinders with L/D > 0.2. Besides of being original, this result was also related to the observation of three regions of aspect ratio, each of them with different behaviors of the motion amplitudes, frequency ratios and force coefficients. For cylinders with L/D > 2.0, the von Kármán wake was the mainly responsible for the oscillatory lift forces. On the other hand, the von Kármán wake was contaminated by the effects coming from the free end of cylinders with 0.5 < L/D < 2.0, mainly by the vortex structures with vorticity in the vertical plane. And for cylinders with 0.2 < L/D <=0.5, the vortex structures at the free end were predominant, thus the only one responsible for the oscillatory lift forces. Finally, in order to understand the source for oscillatory lift forces on cylinders with very low aspect ratio, end-plates were applied and confirmed that VIV in these cases is related to the vortex-shedding around the free end, which indicates an interesting solution for VIM mitigation of platforms.

O aumento das ocorrências de VIM em plataformas flutuantes do tipo \"spar\" e monocoluna serviu de motivação para a investigação dos fundamentos do fenômeno de VIV em cilindros com baixa razão de aspecto e pequena razão de massa. Tal investigação também foi motivada pela necessidade de se preencher lacunas de conhecimento a respeito deste assunto, articularmente por conta da escassa disponibilidade de resultados acerca do VIV em cilindros curtos, bem como pela ausência de modelo fluido que justifique os comportamentos dinâmicos conhecidos. Para o entendimento pretendido, três grupos de experimentos com cilindros dotados de razão de aspecto na faixa 0,1 <= L/D <= 2,0 foram realizados em um canal de água circulante na Escola Politécnica da Universidade de São Paulo, sendo: o primeiro grupo focado nos cilindros curtos estacionários; o segundo nos cilindros curtos de baixa razão de massa, 1,00 <= m* <= 4,36, e dois graus de liberdade; e o grupo final interessado no VIV em cilindros flutuantes, ou seja, razão de massa unitária e seis graus de liberdade. De uma maneira geral, a partir dos resultados aqui obtidos e das comparações com os resultados respectivamente encontrados na literatura, conclui-se que o VIV em cilindros curtos somente acontece se L/D > 0,2. Além de original, a determinação deste valor crítico também identificou outras três regiões com comportamentos fluido-dinâmicos distintos, cada qual marcada por especificidades quanto aos impactos nas amplitudes, frequências e coeficientes de força. Assim sendo, para cilindros com L/D > 2,0 a esteira de von Kármán foi a principal responsável pelas forças sustentação; fato não identificado para os cilindros com 0,5 < L/D < 2,0, onde esta mesma esteira sofreu forte contaminação das estruturas partindo da extremidade livre, principalmente aquelas com vorticidade predominante no plano vertical. Para os cilindros na faixa de 0,2 < L/D <= 0,5, apenas estas últimas estruturas foram responsáveis pelas oscilações de VIV. Finalmente, buscando compreender a origem das forças oscilatórias em cilindros com baixíssima razão de aspecto, \"end-plates\" foram aplicadas e confirmaram que o fenômeno de VIV nestes casos está relacionado à liberação de vórtices junto à extremidade livre, o que indica uma solução interessante para a mitigação do VIM de plataformas. / The increase of VIM occurrences on spar and monocolumn platforms was the motivation to study the vortex-induced vibrations of cylinders with low aspect ratio and small mass ratio under a fundamental perspective. The present work was also motivated by the small number of works in the literature dealing with VIV of cylinders with low aspect ratio, as well as by the scarce concerns about the flow models around this cylinders, which justify the dynamic behaviors observed. Aiming to better understand this problem, three groups of experiments with cylinders of 0.1 <= L/D <= 2.0 were carried out in a recirculating water channel at Escola Politécnica of University of São Paulo, as follow: firstly, the flow around stationary cylinders; secondly, VIV of cylinders with two degrees-of-freedom and 1.00 <= m* <= 4.36. finally, VIV of floating cylinder, thus six degrees-of-freedom. The works concluded that VIV occurs only for cylinders with L/D > 0.2. Besides of being original, this result was also related to the observation of three regions of aspect ratio, each of them with different behaviors of the motion amplitudes, frequency ratios and force coefficients. For cylinders with L/D > 2.0, the von Kármán wake was the mainly responsible for the oscillatory lift forces. On the other hand, the von Kármán wake was contaminated by the effects coming from the free end of cylinders with 0.5 < L/D < 2.0, mainly by the vortex structures with vorticity in the vertical plane. And for cylinders with 0.2 < L/D <=0.5, the vortex structures at the free end were predominant, thus the only one responsible for the oscillatory lift forces. Finally, in order to understand the source for oscillatory lift forces on cylinders with very low aspect ratio, end-plates were applied and confirmed that VIV in these cases is related to the vortex-shedding around the free end, which indicates an interesting solution for VIM mitigation of platforms.

Low-aspect-ratio reinforced concrete (RC) shear walls, characterized by height-to-length ratios of less than two, have been widely used as a seismic force-resisting system (SFRS) in a wide array of structures, ranging from conventional buildings to critical infrastructure systems such as nuclear facilities. Despite their extensive applications, recent research has brought to light the inadequate understanding of their seismic performance, primarily attributed to the intricate nonlinear flexure-shear interaction behaviour unique to these walls. In this respect, the current research dissertation aims to bridge this knowledge gap by conducting a comprehensive evaluation to quantify the seismic performance of low-aspect-ratio RC shear walls when used in different applications. Chapter 2 focuses on low-aspect-ratio RC shear walls that are employed in residential and industrial structures. Considering their significance, the seismic response modification factors of such walls, as defined in various standards, are thoroughly examined and evaluated utilizing the FEMA P695 methodology. The analysis revealed potential deficiencies in the current code-based recommendations for response modification factors. Consequently, a novel set of response modification factors, capable of mitigating the seismic risk of collapse under the maximum considered earthquake, is proposed. Such proposed values can be integrated into the forthcoming revisions of relevant building codes and design standards. While the FEMA P695 methodology offers a comprehensive approach to assessing building seismic performance factors, its practical implementation is associated with many challenges for practicing engineers. Specifically, the methodology heavily relies on resource-intensive and time-consuming incremental dynamic analyses, making it less feasible for routine engineering practices. To enhance its practicality, a data-driven framework is developed in Chapter 3, circumventing the need for such demanding analyses. This framework provides genetic programming-based expressions capable of producing accurate predictions of the median collapse intensities—a key metric in the acceptance criteria of the FEMA P695 methodology, for different structural systems. To demonstrate its use, the developed framework is operationalized to low-aspect-ratio RC shear walls and the predictive expression is evaluated considering several statistical and structural parameters, which showed its adequacy in predicting the median collapse intensities of such walls. Furthermore, the adaptability of this framework is showcased, highlighting its applicability across various SFRSs. Chapters 4 and 5 tackle the scarcity of experimental assessments pertaining to the seismic performance of low-aspect-ratio RC walls in nuclear facilities. The seismic hybrid simulation testing technique is employed herein to merge the simplicity of numerical simulations with the efficiency of experimental tests. Hybrid simulation can overcome obstacles related to physical specimen sizes, limited actuator capacities, and space constraints in most laboratories. In these two chapters, the experimental program delves into evaluating the seismic performance of three two-storey low-aspect-ratio nuclear RC walls under different earthquake levels, including operational, design, and beyond-design-level scenarios. Diverse design configurations, including the use of increased thickness boundary elements and different materials (i.e., normal- and high-strength reinforcement), are considered in such walls to provide a comprehensive understanding of several structural parameters and economic metrics. Key structural parameters, such as the force-displacement responses, multi-storey effects, lateral and rotational stiffnesses, ductility capacities, displacement components, rebar strains, crack patterns and damage sequences, are all investigated to provide direct comparisons between the walls in terms of their seismic performances. Additionally, economic metrics, including the total rebar weights, overall construction costs and the expected seismic repair costs, are considered in order to evaluate the seismic performance of the walls considering an economic perspective. The findings of this experimental investigation are expected to inform future nuclear design standards by enhancing the resilience and safety of their structures incorporating low-aspect-ratio RC shear walls. / Thesis / Doctor of Philosophy (PhD)