Hypersonic interference heating on flat plate with short three-dimensional protuberances

Experiments were conducted to measure the heat flux in the vicinity of a three-dimensional protuberance placed on a flat plate facing a hypersonic flow at zero angle of attack. The effects of flow enthalpy and height of the protuberance on the interference heating in its vicinity were studied. Evidence of disturbed flow with highly three-dimensional characteristics and heightened vorticity was observed near the protrusion. A parametric study by changing the deflection angle of the protuberance was also made. Correlations exist in the open literature for enthalpy values lower than 2  MJ/kg. This effort has yielded a new correlation that is valid for enthalpies up to 6  MJ/kg. The Z-type schlieren technique was used to visualize the flow features qualitatively for one of the flow conditions studied.

Chemical Nonequilibrium Effects on Flow Field for Reusable Launch Vehicles

High temperature chemical non-equilibrium phenomena have a great effect on the flow field around a reentry vehicle. A set of three dimensional Navier-Stokes equations have been solved by implicit finite volume NND scheme. Both ideal gas viscous flow and chemical non-equilibrium flow are calculated for a spherical-cone at a small angle of attack. The results of the two flows have been compared and the effect of chemical non-equilibrium has been analyzed. The effect of wall material's properties, such as catalysis and radiation were studied. The results are in good agreement with the referenced paper.

Analyse der Beifangreduktion durch Gitternetze in der kommerziellen Garnelenfischerei

Trials for the determination of the magnitude of bycatch reduction by sorting grids used in the commercial brown shrimp fishery were carried out from September to December 1997. Trawls with 9 m beam length were used on different fishing grounds in the estuary of the Elbe River near Cuxhaven. The sorting grids tested were made of stainless steel bars spaced at 18, 20, 22, 26 and 30 mm, built into a cylindrical stainless steel frame with a diameter of 65 cm at an angle of attack of 45 degrees. This frame was positioned between the forenet and codend. Simultaneous hauls were made with a trawl of equal construction but without a sorting grid, and the weighed catch components (fish, discard shrimps and commercial size shrimps) separated by means of a riddle were compared. The composition of the sorted out part of the catch of the sorting grid net could be calculated by comparise the corresponding catch components in both the standard trawl and the sorting grid trawl. According to this the total catch of the beam trawl with the sorting grid is reduced by 18 to 38 % depending on the space between the bars. 7 to 31 % of the sorted out part of the catch consists of fish. The use of the sorting grid, however, also leads to losses of 4 to 12 % in Oktober. Per hour of towing this means a loss of 10,3 % commerical size shrimps with a sorting grid of 18 mm space between the bars and of 12,4 % for a 26 mm grid.

Dynamic Stall on Vertical Axis Wind Turbines

In this study the dynamics of flow over the blades of vertical axis wind turbines was investigated using a simplified periodic motion to uncover the fundamental flow physics and provide insight into the design of more efficient turbines. Time-resolved, two-dimensional velocity measurements were made with particle image velocimetry on a wing undergoing pitching and surging motion to mimic the flow on a turbine blade in a non-rotating frame. Dynamic stall prior to maximum angle of attack and a leading edge vortex development were identified in the phase-averaged flow field and captured by a simple model with five modes, including the first two harmonics of the pitch/surge frequency identified using the dynamic mode decomposition. Analysis of these modes identified vortical structures corresponding to both frequencies that led the separation and reattachment processes, while their phase relationship determined the evolution of the flow.

Detailed analysis of the leading edge vortex found multiple regimes of vortex development coupled to the time-varying flow field on the airfoil. The vortex was shown to grow on the airfoil for four convection times, before shedding and causing dynamic stall in agreement with 'optimal' vortex formation theory. Vortex shedding from the trailing edge was identified from instantaneous velocity fields prior to separation. This shedding was found to be in agreement with classical Strouhal frequency scaling and was removed by phase averaging, which indicates that it is not exactly coupled to the phase of the airfoil motion.

The flow field over an airfoil undergoing solely pitch motion was shown to develop similarly to the pitch/surge motion; however, flow separation took place earlier, corresponding to the earlier formation of the leading edge vortex. A similar reduced-order model to the pitch/surge case was developed, with similar vortical structures leading separation and reattachment; however, the relative phase lead of the separation mode, corresponding to earlier separation, necessitated that a third frequency to be incorporated into the reattachment mode to provide a relative lag in reattachment.

Finally, the results are returned to the rotating frame and the effects of each flow phenomena on the turbine are estimated, suggesting kinematic criteria for the design of improved turbines.

The unsteady forces on slender delta wing hydrofoils oscillating in heave

The investigations described herein are both experimental and theoretical. An experimental technique is described by which the models tested could be oscillated sinusoidally in heave. The apparatus used to gather the unsteady lift, drag and pitching moment data is also described.

The models tested were two flat delta wings with apex angles of 15° and 30° and they had sharp leading edges to insure flow separation. The models were fabricated from 0.25 inch aluminum plate and were approximately one foot in length.

Three distinct types of flow were investigated: 1) fully wetted, 2) ventilated and 3) planing. The experimental data are compared with existing theories for steady motions in the case of fully wetted delta wings. Ventilation measurements, made only for the 30° model at 20° angle of attack, of lift and drag are presented.

A correction of the theory proposed by M.P. Tulin for high speed planing of slender bodies is presented and it is extended to unsteady motions. This is compared to the experimental measurements made at 6° and 12° angle of attack for the two models previously described.

This is the first extensive measurement of unsteady drag for any shape wing, the first measurement of unsteady planing forces, the first quantitative documentation of unstable oscillations near a free surface, and the first measurements of the unsteady forces on ventilated delta wings. The results of these investigations, both theoretical and experimental, are discussed and further investigations suggested.

Lift and the leading-edge vortex

Flapping wings often feature a leading-edge vortex (LEV) that is thought to enhance the lift generated by the wing. Here the lift on a wing featuring a leading-edge vortex is considered by performing experiments on a translating flat-plate aerofoil that is accelerated from rest in a water towing tank at a fixed angle of attack of 15°. The unsteady flow is investigated with dye flow visualization, particle image velocimetry (PIV) and force measurements. Leading-and trailing-edge vortex circulation and position are calculated directly from the velocity vectors obtained using PIV. In order to determine the most appropriate value of bound circulation, a two-dimensional potential flow model is employed and flow fields are calculated for a range of values of bound circulation. In this way, the value of bound circulation is selected to give the best fit between the experimental velocity field and the potential flow field. Early in the trajectory, the value of bound circulation calculated using this potential flow method is in accordance with Kelvin's circulation theorem, but differs from the values predicted by Wagner's growth of bound circulation and the Kutta condition. Later the Kutta condition is established but the bound circulation remains small; most of the circulation is contained instead in the LEVs. The growth of wake circulation can be approximated by Wagner's circulation curve. Superimposing the non-circulatory lift, approximated from the potential flow model, and Wagner's lift curve gives a first-order approximation of the measured lift. Lift is generated by inertial effects and the slow buildup of circulation, which is contained in shed vortices rather than bound circulation. © 2013 Cambridge University Press.

On high-frequency noise scattering by aerofoils in flow

Abstract A theoretical model is developed for the sound scattered when a sound wave is incident on a cambered aerofoil at non-zero angle of attack. The model is based on the linearization of the Euler equations about a steady subsonic flow, and is an adaptation of previous work which considered incident vortical disturbances. Only high-frequency sound waves are considered. The aerofoil thickness, camber and angle of attack are restricted such that the steady flow past the aerofoil is a small perturbation to a uniform flow. The singular perturbation analysis identifies asymptotic regions around the aerofoil; local 'inner' regions, which scale on the incident wavelength, at the leading and trailing edges of the aerofoil; Fresnel regions emanating from the leading and trailing edges of the aerofoil due to the coalescence of singularities and points of stationary phase; a wake transition region downstream of the aerofoil leading and trailing edge; and an outer region far from the aerofoil and wake. An acoustic boundary layer on the aerofoil surface and within the transition region accounts for the effects of curvature. The final result is a uniformly-valid solution for the far-field sound; the effects of angle of attack, camber and thickness are investigated. © 2013 Cambridge University Press.

Simulação numérica da interação entre uma nuvem incidente de vórtices e uma aerofólio através do método dos vórtices

The study of aerodynamic loading variations has many engineering applications, including helicopter rotor blades, wind turbines and turbo machinery. This work uses a Vortex Method to make a lagrangian description of the a twodimensional airfoil/ incident wake vortex interaction. The flow is incompressible, newtonian, homogeneus and the Reynolds Number is 5x105 .The airfoil is a NACA 0018 placed a angle of attack of the 0° and 5°simulates with the Painel Method with a constant density vorticity panels and a generation poit is near the painel. The protector layer is created does not permit vortex inside the body. The vortex Lamb convection is realized with the Euler Method (first order) and Adans-Bashforth (second order). The Random Walk Method is used to simulate the diffusion. The circular wake has 366 vortex all over positive or negative vorticity located at different heights with respect to the airfoil chord. The Lift was calculated based in the algorithm created by Ricci (2002). This simulation uses a ready algorithm vatidated with single body does not have a incident wake. The results are compared with a experimental work The comparasion concludes that the experimental results has a good agrement with this papper

Análisis de la influencia del borde de salida abierto en perfiles aerodinámicos a bajos números de Reynolds

El objetivo del presente trabajo es analizar la influencia que tiene sobre el comportamiento aerodinámico del perfil el hecho de que este presente un borde de salida más grueso que el perfil original del que se partía. Este estudio se ha centrado fundamentalmente en la influencia sobre su sustentación aerodinámica, resistencia aerodinámica y, especialmente, sobre la eficiencia aerodinámica del perfil, es decir sobre la relación entre la sustentación y la resistencia aerodinámica. También se ha analizado su influencia en otros aspectos aerodinámicos de los perfiles, como la entrada en pérdida, el ángulo de ataque de sustentación máxima, el ángulo de ataque de eficiencia máxima, el coeficiente de momento aerodinámico y la posición del centro aerodinámico. Estas imperfecciones en el borde de salida pueden aparecer en algunos procesos de fabricación de determinados elementos aerodinámicos, como alas de aviones no tripulados o palas de aeroturbina. Este fenómeno no ha sido analizado en profundidad en la literatura científica, aunque si que se ha analizado por varios autores la influencia sobre el perfil con el borde de salida truncado, o perfiles con la parte final regruesada, utilizados en otras aplicaciones. Para la realización de este estudio se han analizado perfiles de distinto tipo, laminares y no laminares, perfiles simétricos y con curvatura, así como perfiles con distinto espesor, a fin de comparar el grado de influencia del fenómeno estudiado sobre cada tipo de perfil para comparar su grado de sensibilidad a dicha anomalía geométrica. El estudio se ha realizado experimentalmente utilizando una cámara de ensayos diseñada específicamente a tal efecto, así como una balanza electrónica para medir las fuerzas y los momentos sobre el perfil, y un escáner de presiones para medir la distribución de presiones en determinados casos. También se ha abordado el estudio del comportamiento de perfiles con borde de salida más grueso que el nominal pero redondeado en vez de romo, con el objeto de analizar la eficacia de redondear el borde de salida, que es uno de los métodos que se puede utilizar para mitigar este efecto. Por otro lado, como el comportamiento de los perfiles aerodinámicos tiene una fuerte dependencia del número de Reynolds, el estudio se ha centrado en el análisis del comportamiento a bajos números de Reynolds debido a su uso reciente en una amplia gama de aplicaciones, desde vehículos aéreos no tripulados (UAV) hasta palas de aeroturbinas de baja potencia, e incluso debido a su uso potencial en aeronaves diseñadas para volar en atmósferas de baja densidad como la que existe en Marte. El interés de este estudio está orientado al establecimiento de criterios para cuantificar la influencia que tiene el hecho de que el borde de salida sea más grueso que el nominal en la degradación de su eficiencia aerodinámica máxima, con el objeto de poder establecer los límites de aceptación o rechazo de estas piezas una vez fabricadas, según el tipo de perfil aerodinámico utilizado. Del resultado del análisis de los casos estudiados se puede concluir que según aumenta el espesor del borde de salida, dentro del intervalo de estudio, la sustentación aerodinámica aumenta, así como la sustentación máxima, pero aumenta en mayor proporción la resistencia aerodinámica, por lo que se produce una reducción de la eficiencia aerodinámica, en particular de su valor máximo. Por otro lado, el hecho de redondear el borde de salida del perfil ayuda ligeramente a reducir este efecto. ABSTRACT The aim of this thesis is to analyze the effects of airfoil trailing edges thickness when this is thicker than the airfoil nominal. Several factors may lead to an airfoil trailing edge being thicker than the nominal airfoil, and this may affect various aerodynamic parameters. This study has focus on its influence on the airfoil’s aerodynamic lift, drag and, particularly on the aerodynamic efficiency of the airfoil, that is, the relationship between the aerodynamic lift and drag. It has also been studied how this fact may alter some other aerodynamic aspects of airfoils, such as stall, angle of attack of maximum lift, angle of maximum efficiency, aerodynamic moment coefficient and aerodynamic center position. These imperfections in the trailing edge may appear in some manufacturing processes of certain aerodynamic elements, such as unmanned aircraft wings or wind turbine blades. This phenomenon has not been deeply analyzed in the literature, although several authors have discussed its influence on airfoil with truncated trailing edge, or airfoils with thickened end, used in other applications. Various types of airfoils have been analyzed, laminar and non-laminar, symmetric and curved airfoils, and airfoils with different thickness, in order to compare the degree of influence of the phenomenon studied on each airfoil type and thus, to estimate the degree of sensitivity to the anomaly geometry. The study was carried out experimentally using a test chamber designed specifically for this purpose, as well as an electronic balance to measure the forces and moments on the airfoil, and a pressure scanner to measure distribution of pressures in certain cases. It has also been investigated the behavior of airfoils with trailing edge thicker than the nominal, but rounded instead of blunt, in order to analyze the effectiveness of the trailing edge rounding, which is one of the methods that can be used to mitigate this phenomenon. Moreover, as the behavior of the airfoil is highly dependent on the Reynolds number, the study has been focused on the analysis of the behavior at low Reynolds numbers due to recent use of low Reynolds numbers airfoils in a wide range of applications, from unmanned aerial vehicles (UAV) to low power wind turbine blades, or even due to their potential use in aircraft designed to fly in low density atmospheres as the one existing in Mars. The main purpose of this research is to establish a set of criteria for quantifying the influence that a thicker-than–nominal-trailing edge has in the degradation of maximum aerodynamic efficiency, aiming at establishing the acceptance limits for these pieces when they are manufactured, according to the type of airfoil used. Based on the results obtained from the analysis of the cases under study it can be concluded that increasing the thickness of the trailing edge, within the range of study, increases aerodynamic lift, as well as maximum lift, but the aerodynamic drag increases in a higher proportion, and consequently there is a reduction of aerodynamic efficiency, particularly, of its maximum value. On the other hand, rounding the trailing edge of the airfoil slightly helps to reduce this effect.

Fenómenos de galope en piezas prismáticas con sección en H

El objetivo de esta Tesis es el estudio sistemático del fenómeno aeroelástico de galope de una viga prismática con sección transversal en H. En particular, se pretende analizar la influencia de determinados parámetros geométricos que definen la geometría de la sección y el efecto del ángulo de ataque de la corriente sobre la estabilidad del fenómeno de oscilación. El interés en el estudio de esta forma de la sección transversal de una viga se basa en el hecho de que, con cierta frecuencia, se sigue utilizando, por su buen comportamiento estructural, en construcciones civiles como tableros y tirantes de puentes de gran longitud, señalizaciones, luminarias y, en general, en grandes estructuras metálicas. Los parámetros geométricos seleccionados para su estudio son tres: el espesor de las dos alas verticales, su porosidad y el espesor de sendas ranuras en la zona de unión entre el alma y las alas de la sección. Inicialmente se han realizado ensayos estáticos en un túnel aerodinámico con objeto de obtener las cargas aerodinámicas y poder aplicar el criterio casi-estático de Glauert - Den Hartog. En estos ensayos, se han medido tanto las fuerzas de sustentación y resistencia aerodinámicas como las distribuciones de presiones en la superficie de la zona central de la sección. Posteriormente, se han realizado ensayos de visualización de flujo, utilizando un túnel de humos, para poder comprender mejor el comportamiento físico del aire alrededor del cuerpo. El estudio estático se ha completado realizando ensayos con PIV, que permiten realizar una medida precisa de la velocidad del campo fluido. Por último, se han realizado ensayos dinámicos en otro túnel aerodinámico con objeto de contrastar la aplicabilidad del criterio casi-estático, la velocidad de inicio de galope y la amplitud de las oscilaciones producidas. Los resultados muestran que el espesor de las alas verticales, aunque modifica apreciablemente la magnitud de las cargas aerodinámicas, no afecta sustancialmente a la estabilidad a galope, mientras que su porosidad sí ejerce un control efectivo que permite reducir este fenómeno e incluso evitarlo, en determinados casos. En todas las situaciones el criterio de Glauert-Glauert - Den Hartog ha resultado ser aplicable y, en ocasiones, más restrictivo que los resultados obtenidos en ensayos dinámicos. La presencia de una ranura en la zona de unión entre el alma y las dos alas, o su combinación con la porosidad en las alas, reduce la intensidad de galope, incrementando la velocidad crítica de su inicio, pero no logra hacer que desaparezca, como se justificará en el desarrollo del trabajo. ABSTRACT Galloping is a type of aeroelastic instability characterized by a large amplitude oscillation at the natural frequency of the structure, producing normal motion to wind. It usually occurs in slender bodies lightly damped at sufficiently high speeds. In this thesis an experimental study has been developed on the galloping instability of a beam with H cross section, which is inscribed in a rectangle with a slender 1: 2. A systematic study has been carried out of the influence of three different geometric parameters on galloping, in the range of 0 to 90° angle of attack of the incoming stream. These parameters are the thickness of the flanges of the section, the porosity of the flanges, the thickness of two slots along the span, in the area between the flange and the central core of the section, and the combination effect of the last two parameters. First of all, static tests have been performed in a wind tunnel to determine the lift and drag forces by using a balance and then the quasi-static stability criterion due to Glauert-Den Hartog has been determined. Later, to better understand and verify the results previously obtained, it has also been tested the pressure distribution on the surface of the model, flow visualization in a second, smoke, wind tunnel, and Particle Image Velocimetry (PIV) study of the flow around the section, in a third tunnel. Finally, dynamic tests have been performed, on a fourth wind tunnel, for determining the amplitude and frequency of the oscillations in each case. The results have been collected in stability diagrams for each geometric parameter studied. These results show that the more critical angles of attack of the stream for galloping behavior are close to 0 and 90º. It has been found that the thickness of the flanges, although changes the galloping behavior on the section, does not reduce it substantially. However, the porosity in the flanges has been proved to be an efficient control mechanism on galloping, and even above 40% porosity, it disappears. The thickness of the slot studied and its combination with the porosity in the flanges in some cases reduces the aerodynamic forces appreciably but fail to prevent galloping at all angles of attack.

Investigación de fenómenos de galope en cuerpos de diversa sección transversal

Los fenómenos aeroelásticos son relativamente frecuentes en las construcciones civiles modernas como edificios de oficinas, terminales de aeropuertos o fábricas. En este tipo de arquitectura aparecen con frecuencia estructuras flexibles sometidas a la acción del viento, como por ejemplo persianas formadas por láminas con distintos perfiles. Uno de estos perfiles es el perfil en Z, formado por un elemento central y dos alas laterales. Las inestabilidades de tipo galope se determinan en la práctica utilizando el criterio Glauert-Den Hartog. Este criterio precisa de la predicción exacta de la dependencia de los coeficientes aerodinámicos del ángulo de ataque. En esta tesis se presenta un estudio sistemático, tanto por métodos experimentales como numéricos de una familia completa de perfiles en Z que permite determinar sus regiones de inestabilidad frente al galope. Los análisis numéricos han sido validados con ensayos estáticos realizados en túnel de viento. Para la parte numérica se ha utilizado el código DLR TAU, que es un código de amplia utilización en la industria aeronáutica europea. En esta tesis se enfoca sobre todo a la predicción del galope en este tipo de perfiles en Z. Los resultados se presentan en forma de mapas de estabilidad. A lo largo del trabajo se realizan también comparaciones entre resultados numéricos y experimentales para varios niveles de detalle de las mallas empleadas y diversos modelos de turbulencia. ABSTRACT Aeroelastic effects are relatively common in the design of modern civil constructions such as office blocks, airport terminal buildings, and factories. Typical flexible structures exposed to the action of wind are shading devices, normally slats or louvers. A typical cross-section for such elements is a Z-shaped profile,made out of a central web and two-sidewings. Galloping instabilities are often determined in practice using the Glauert-DenHartog criterion.This criterion relies on accurate predictions of the dependence of the aerodynamic force coefficients with the angle of attack. The results of a parametric analysis based on both experimental and numerical analysis and performed on different Z-shaped louvers to determine translational galloping instability regions are presented in this thesis. These numerical analysis results have been validated with a parametric analysis of Z-shaped profiles based on static wind tunnel tests. In order to perform this validation, the DLR TAU Code, which is a standard code within the European aeronautical industry, has been used. This study highlights the focus on the numerical prediction of the effect of galloping, which is shown in a visible way, through stability maps. Comparisons between numerical and experimental data are presented with respect to various meshes and turbulence models.

Aerodynamic database error filtering via high order singular value decomposition

Esta Tesis presenta un nuevo método para filtrar errores en bases de datos multidimensionales. Este método no precisa ninguna información a priori sobre la naturaleza de los errores. En concreto, los errrores no deben ser necesariamente pequeños, ni de distribución aleatoria ni tener media cero. El único requerimiento es que no estén correlados con la información limpia propia de la base de datos. Este nuevo método se basa en una extensión mejorada del método básico de reconstrucción de huecos (capaz de reconstruir la información que falta de una base de datos multidimensional en posiciones conocidas) inventado por Everson y Sirovich (1995). El método de reconstrucción de huecos mejorado ha evolucionado como un método de filtrado de errores de dos pasos: en primer lugar, (a) identifica las posiciones en la base de datos afectadas por los errores y después, (b) reconstruye la información en dichas posiciones tratando la información de éstas como información desconocida. El método resultante filtra errores O(1) de forma eficiente, tanto si son errores aleatorios como sistemáticos e incluso si su distribución en la base de datos está concentrada o esparcida por ella. Primero, se ilustra el funcionamiento delmétodo con una base de datosmodelo bidimensional, que resulta de la dicretización de una función transcendental. Posteriormente, se presentan algunos casos prácticos de aplicación del método a dos bases de datos tridimensionales aerodinámicas que contienen la distribución de presiones sobre un ala a varios ángulos de ataque. Estas bases de datos resultan de modelos numéricos calculados en CFD. ABSTRACT A method is presented to filter errors out in multidimensional databases. The method does not require any a priori information about the nature the errors. In particular, the errors need not to be small, neither random, nor exhibit zero mean. Instead, they are only required to be relatively uncorrelated to the clean information contained in the database. The method is based on an improved extension of a seminal iterative gappy reconstruction method (able to reconstruct lost information at known positions in the database) due to Everson and Sirovich (1995). The improved gappy reconstruction method is evolved as an error filtering method in two steps, since it is adapted to first (a) identify the error locations in the database and then (b) reconstruct the information in these locations by treating the associated data as gappy data. The resultingmethod filters out O(1) errors in an efficient fashion, both when these are random and when they are systematic, and also both when they concentrated and when they are spread along the database. The performance of the method is first illustrated using a two-dimensional toymodel database resulting fromdiscretizing a transcendental function and then tested on two CFD-calculated, three-dimensional aerodynamic databases containing the pressure coefficient on the surface of a wing for varying values of the angle of attack. A more general performance analysis of the method is presented with the intention of quantifying the randomness factor the method admits maintaining a correct performance and secondly, quantifying the size of error the method can detect. Lastly, some improvements of the method are proposed with their respective verification.

Intensificação da transferência de calor e otimização de trocadores de calor compactos tipo venezianas com geradores de vórtices tipo delta-winglets.

Esta pesquisa visa a análise da contribuição de cinco variáveis de entrada e a otimização do desempenho termo-hidráulico de trocadores de calor com venezianas combinados com geradores de vórtices delta-winglets. O desempenho termohidráulico de duas geometrias distintas, aqui nomeadas por GEO1 e GEO2, foram avaliadas. Smoothing Spline ANOVA foi usado para avaliar a contribuição dos parâmetros de entrada na transferência de calor e perda de carga. Considerando aplicação automotiva, foram investigados números de Reynolds iguais a 120 e 240, baseados no diâmetro hidráulico. Os resultados indicaram que o ângulo de venezianas é o maior contribuidor para o aumento do fator de atrito para GEO1 e GEO2, para ambos os números de Reynolds. Para o número de Reynolds menor, o parâmetro mais importante em termos de transferência de calor foi o ângulo das venezianas para ambas as geometrias. Para o número de Reynolds maior, o ângulo de ataque dos geradores de vórtices posicionados na primeira fileira é o maior contribuidor para a tranfesferência de calor, no caso da geometria GEO1, enquanto que o ângulo de ataque dos geradores de vórtices na primeira fileira foi tão importante quanto os ângulos das venezianas para a geometria GEO2. Embora as geometrias analisadas possam ser consideradas como técnicas compostas de intensificação da transferência de calor, não foram observadas interações relevantes entre ângulo de venezianas e parâmetros dos geradores de vórtices. O processo de otimização usa NSGA-II (Non-Dominated Sorting Genetic Algorithm) combinado com redes neurais artificiais. Os resultados mostraram que a adição dos geradores de vórtices em GEO1 aumentaram a transferência de calor em 21% e 23% com aumentos na perda de carga iguais a 24,66% e 36,67% para o menor e maior números de Reynolds, respectivamente. Para GEO2, a transferência de calor aumentou 13% e 15% com aumento na perda de carga de 20,33% e 23,70%, para o menor e maior número de Reynolds, respectivamente. As soluções otimizadas para o fator de Colburn mostraram que a transferência de calor atrás da primeira e da segunda fileiras de geradores de vórtices tem a mesma ordem de magnitude para ambos os números de Reynolds. Os padrões de escoamento e as características de transferência de calor das soluções otimizadas apresentaram comportamentos vi particulares, diferentemente daqueles encontrados quando as duas técnicas de intensificação de transferência de calor são aplicadas separadamente.

Estudo numérico do efeito de blocagem hidrodinâmica em um túnel de cavitação sobre o escoamento ao redor de um submarino.

O projeto de submarinos é um tema que vem se desenvolvendo há muitos anos. No Brasil, vivemos um momento de pleno avanço na área, sendo encabeçado pela Marinha do Brasil com o desenvolvimento do primeiro submarino de propulsão nuclear brasileiro. No decorrer desse projeto, diversos estudos devem ser desenvolvidos, dentre eles, ensaios com modelos em escala, que serão realizados em um túnel de cavitação. Durante estes experimentos, espera-se que surjam diversas fontes de incerteza, que podem comprometer os resultados obtidos, destacando-se o efeito de blocagem hidrodinâmica. Nesse contexto, esta dissertação apresenta uma investigação do fenômeno de blocagem no modelo de submarino DARPA SUBOFF na seção de testes de um túnel de cavitação. Para isso, simulações tridimensionais de média de Reynolds (RANS) foram realizadas para o modelo de submarino posicionado no túnel (sob blocagem) e sob condição de águas profundas (referência), para diferentes ângulos de ataque e número de Reynolds (Re) constante. Coeficientes de força e momento hidrodinâmicos foram obtidos e os métodos de correção de blocagem clássico e WICS foram empregados para obter fatores que pudessem corrigir esses valores. A eficiência de cada método foi avaliada comparando os valores corrigidos com os de referência. Os resultados mostraram que ambos métodos de correção são eficientes na recuperação de coeficientes de força e momento hidrodinâmicos para razões de blocagem inferiores a 10%, mas ressalvas são feitas quanto à utilização de cada um desses métodos, sendo o método clássico indicado para o estudo de geometrias simples e o método WICS para modelos mais complexos. Paralelamente, a topologia do escoamento ao redor do submarino foi estudada através do método dos pontos críticos, para avaliar se a blocagem hidrodinâmica pode causar alterações nas estruturas presentes no escoamento. A análise topológica permitiu avaliar a evolução nas estruturas do escoamento para os ângulos de ataque e Re simulados. Foram capturadas as linhas de separação no corpo e avaliada sua relação com a tensão de cisalhamento ao longo do casco. A blocagem hidrodinâmica não causou alterações drásticas na topologia do escoamento.

Wind Shear, Gust, and Yaw-Induced Dynamic Stall on Wind-Turbine Blades

This study examined the effect of a spanwise angle of attack gradient on the growth and stability of a dynamic stall vortex in a rotating system. It was found that a spanwise angle of attack gradient induces a corresponding spanwise vorticity gradient, which, in combination with spanwise flow, results in a redistribution of circulation along the blade. Specifically, when modelling the angle of attack gradient experienced by a wind turbine at the 30% span position during a gust event, the spanwise vorticity gradient was aligned such that circulation was transported from areas of high circulation to areas of low circulation, increasing the local dynamic stall vortex growth rate, which corresponds to an increase in the lift coefficient, and a decrease in the local vortex stability at this point. Reversing the relative alignment of the spanwise vorticity gradient and spanwise flow results in circulation transport from areas of low circulation generation to areas of high circulation generation, acting to reduce local circulation and stabilise the vortex. This circulation redistribution behaviour describes a mechanism by which the fluctuating loads on a wind turbine are magnified, which is detrimental to turbine lifetime and performance. Therefore, an understanding of this phenomenon has the potential to facilitate optimised wind turbine design.