Análisis de la influencia de imperfecciones en el borde de ataque en perfiles aerodinámicos a bajos números de Reynolds

En esta tesis se ha analizado la influencia que tienen ciertas imperfecciones en el borde de ataque de un perfil aerodinámico sobre el comportamiento aerodinámico general del mismo, centrándose fundamentalmente en la influencia sobre el coeficiente de sustentación máxima, coeficiente de resistencia y sobre la eficiencia aerodinámica del perfil, es decir sobre la relación entre la sustentación y la resistencia aerodinámicas. También se ha analizado su influencia en otros aspectos, como la entrada en pérdida, ángulo de ataque de sustentación máxima, ángulo de ataque de eficiencia máxima, coeficiente de momento aerodinámico y posición del centro aerodinámico. Estos defectos de forma en el borde de ataque pueden aparecer en algunos procesos de fabricación de determinados elementos aerodinámicos, como pueden ser las alas de pequeños aviones no tripulados o las palas de aeroturbina. Los perfiles se ha estudiado 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 aeroturbina de baja potencia, e incluso debido a su potencial utilización en aeronaves diseñadas para volar en atmósferas de baja densidad. El objeto de estudio de esta tesis no ha sido analizado en profundidad en la literatura científica, aunque sí que se ha estudiado por varios autores el comportamiento de perfiles a bajos números de Reynolds, con ciertas protuberancias sobre su superficie o también con formación de hielo en el borde de ataque. Para la realización de este estudio se han analizado perfiles de distinto tipo, perfiles simétricos y con curvatura, perfiles laminares, y todos ellos con igual o distinto espesor, con el objeto de obtener y comparar la influencia del fenómeno estudiado sobre cada tipo de perfil y así analizar su grado de sensibilidad a estas imperfecciones en la geometría del borde de ataque. Este trabajo ha sido realizado experimentalmente utilizando una túnel aerodinámico diseñado 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 sobre la superficie de los perfiles en determinados casos de interés. La finalidad de este estudio está orientada al establecimiento de criterios para cuantificar la influencia en la aerodinámica del perfil que tiene el hecho de que el borde de ataque presente una discontinuidad geométrica, con el objeto de poder establecer los límites de aceptación o rechazo de estas piezas en el momento de ser fabricadas. Del análisis de los casos estudiados se puede concluir que según aumenta el tamaño de la imperfección del borde de ataque, la sustentación aerodinámica máxima en general disminuye, al igual que la eficiencia aerodinámica máxima, pues la resistencia aerodinámica aumenta. Sin embargo, en algunos casos, para pequeños defectos se produce un efecto contrario. La sustentación máxima aumenta apreciablemente sin apenas pérdida de eficiencia aerodinámica máxima. ABSTRACT The aim of this thesis is to analyze the effects of leading edge imperfections on the aerodynamic characteristics of airfoils at low Reynolds numbers. The leading edge imperfection here considered being a slight displacement of half airfoil with respect to the other. This study has focus on its influence on the airfoil’s aerodynamic lift, drag and 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 leading edge may appear in some manufacturing processes of certain aerodynamic elements, such as unmanned aircraft wings or wind turbine blades. The study has 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. This phenomenon has not been deeply analyzed in the literature, although several authors have discussed on airfoils at low Reynolds number, with leading edge protuberances or airfoils with ice accretions. 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. The main purpose of this research is to establish a criteria for quantifying the influence that a slight displacement of half aerofoil with respect to the other has in the degradation of aerodynamics characteristics, 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 displacements, within the range of study, decreases maximum aerodynamic lift, but the aerodynamic drag increases, and consequently there is a reduction of aerodynamic efficiency. However, in some cases, for small defects opposite effect occurs. The maximum lift increases significantly with little loss of maximum aerodynamic efficiency.

Chaos in non lineal Alfven waves using the DNLS equations

The electro-dynamical tethers emit waves in structured denominated Alfven wings. The Derivative Nonlineal Schrödinger Equation (DNLS) possesses the capacity to describe the propagation of circularly polarized Alfven waves of finite amplitude in cold plasmas. The DNLS equation is truncated to explore the coherent, weakly nonlinear, cubic coupling of three waves near resonance, one wave being linearly unstable and the other waves damped. In this article is presented a theoretical and numerical analysis when the growth rate of the unstable wave is next to zero considering two damping models: Landau and resistive. The DNLS equation presents a chaotic dynamics when is consider only three wave truncation. The evolution to chaos possesses three routes: hard transition, period-doubling and intermittence of type I.

Vibro-acoustic analysis of spacecraft structures with thin air layers

Esta Tesis presenta un estudio sobre el comportamiento vibroacústico de estructuras espaciales que incluyen capas de aire delgadas, así como sobre su modelización numérica. Las capas de aire pueden constituir un elemento fundamental en estos sistemas, como paneles solares plegados, que se consideran el caso de estudio en este trabajo. Para evaluar la influencia de las capas de aire en la respuesta dinámica del sistema se presenta el uso de modelos unidimensionales. La modelización de estos sistemas se estudia para los rangos de baja y alta frecuencia. En el rango de baja frecuencia se propone un conjunto de estrategias de simulación basadas en técnicas numéricas que se utilizan habitualmente en la industria aeroespacial para facilitar la aplicación de los resultados de la Tesis en los modelos numéricos actuales. Los resultados muestran el importante papel de las capas de aire en la respuesta del sistema. El uso de modelos basados en elementos finitos o de contorno para estos elementos proporciona resultados equivalentes aunque la aplicabilidad de estos últimos puede estar condicionada por la geometría del problema. Se estudia asimismo el uso del Análisis Estadístico de la Energía (SEA) para estos elementos. Una de las estrategias de simulación propuestas, que incluye una formulación energética para el aire que rodea a la estructura, se propone como estimador preliminar de la respuesta del sistema y sus frecuencias propias. Para el rango de alta frecuencia, se estudia la influencia de la definición del propio modelo SEA. Se presenta el uso de técnicas de reducción para determinar una matriz de pérdidas SEA reducida para definiciones incompletas del sistema (si algún elemento que interactúa con el resto no se incluye en el modelo). Esta nueva matriz tiene en cuenta la contribución de las subestructuras que no se consideran parte del modelo y que suelen ignorarse en el procedimiento habitual para reducir el tamaño del mismo. Esta matriz permite también analizar sistemas que incluyen algún componente con problemas de accesibilidad para medir su respuesta. Respecto a la determinación de los factores de pérdidas del sistema, se presenta una metodología que permite abordar casos en los que el método usual, el Método de Inyección de Potencia (PIM), no puede usarse. Se presenta un conjunto de métodos basados en la técnicas de optimización y de actualización de modelos para casos en los que no se puede medir la respuesta de todos los elementos del sistema y también para casos en los que no todos los elementos pueden ser excitados, abarcando un conjunto de casos más amplio que el abordable con el PIM. Para ambos rangos de frecuencia se presentan diferentes casos de análisis: modelos numéricos para validar los métodos propuestos y un panel solar plegado como caso experimental que pone de manifiesto la aplicación práctica de los métodos presentados en la Tesis. ABSTRACT This Thesis presents an study on the vibro-acoustic behaviour of spacecraft structures with thin air layers and their numerical modelling. The air layers can play a key role in these systems as solar wings in folded configuration that constitute the study case for this Thesis. A method based on one-dimensional models is presented to assess the influence of the air layers in the dynamic response of the system. The modelling of such systems is studied for low and high frequency ranges. In the low frequency range a set of modelling strategies are proposed based on numerical techniques used in the industry to facilitate the application of the results in the current numerical models. Results show the active role of the air layers in the system response and their great level of influence. The modelling of these elements by means of Finite Elements (FE) and Boundary Elements (BE) provide equivalent results although the applicability of BE models can be conditioned by the geometry of the problem. The use of Statistical Energy Analysis (SEA) for these systems is also presented. Good results on the system response are found for models involving SEA beyond the usual applicability limit. A simulation strategy, involving energetic formulation for the surrounding fluid is proposed as fast preliminary approach for the system response and the coupled eigenfrequencies. For the high frequency range, the influence of the definition of the SEA model is presented. Reduction techniques are used to determine a Reduced SEA Loss Matrix if the system definition is not complete and some elements, which interact with the rest, are not included. This new matrix takes into account the contribution of the subsystems not considered that are neglected in the usual approach for decreasing the size of the model. It also allows the analysis of systems with accessibility restrictions on some element in order to measure its response. Regarding the determination of the loss factors of a system, a methodology is presented for cases in which the usual Power Injection Method (PIM) can not be applied. A set of methods are presented for cases in which not all the subsystem responses can be measured or not all the subsystems can be excited, as solar wings in folded configuration. These methods, based on error minimising and model updating techniques can be used to calculate the system loss factors in a set of cases wider than the PIM’s. For both frequency ranges, different test problems are analysed: Numerical models are studied to validate the methods proposed; an experimental case consisting in an actual solar wing is studied on both frequency ranges to highlight the industrial application of the new methods presented in the Thesis.

Galloping instabilities of Z-shaped shading louvers

Modern design of civil constructions such as office blocks, airport terminal buildings, factories, etc. incorporates more and more environmental considerations that lead to, amongst other elements, the use of glazed façades with shading devices to optimize energy consumption. These shading devices, normally slats or louvers, are very flexible structures exposed to the action of wind, and therefore aeroelastic effects such as galloping must be taken into account in their design. A typical cross-section for such elements is a Z-shaped profile made out of a central web and two side wings. The results of a parametric analysis based on static wind tunnel tests and performed on different Z-shaped louvers to determine translational galloping instability regions are presented in this paper.

NURBS-Based Geometry Parameterization for Aerodynamic Shape Optimization

La motivación de esta tesis es el desarrollo de una herramienta de optimización automática para la mejora del rendimiento de formas aerodinámicas enfocado en la industria aeronáutica. Este trabajo cubre varios aspectos esenciales, desde el empleo de Non-Uniform Rational B-Splines (NURBS), al cálculo de gradientes utilizando la metodología del adjunto continuo, el uso de b-splines volumétricas como parámetros de diseño, el tratamiento de la malla en las intersecciones, y no menos importante, la adaptación de los algoritmos de la dinámica de fluidos computacional (CFD) en arquitecturas hardware de alto paralelismo, como las tarjetas gráficas, para acelerar el proceso de optimización. La metodología adjunta ha posibilitado que los métodos de optimización basados en gradientes sean una alternativa prometedora para la mejora de la eficiencia aerodinámica de los aviones. La formulación del adjunto permite calcular los gradientes de una función de coste, como la resistencia aerodinámica o la sustentación, independientemente del número de variables de diseño, a un coste computacional equivalente a una simulación CFD. Sin embargo, existen problemas prácticos que han imposibilitado su aplicación en la industria, que se pueden resumir en: integrabilidad, rendimiento computacional y robustez de la solución adjunta. Este trabajo aborda estas contrariedades y las analiza en casos prácticos. Como resumen, las contribuciones de esta tesis son: • El uso de NURBS como variables de diseño en un bucle de automático de optimización, aplicado a la mejora del rendimiento aerodinámico de alas en régimen transónico. • El desarrollo de algoritmos de inversión de punto, para calcular las coordenadas paramétricas de las coordenadas espaciales, para ligar los vértices de malla a las NURBS. • El uso y validación de la formulación adjunta para el calculo de los gradientes, a partir de las sensibilidades de la solución adjunta, comparado con diferencias finitas. • Se ofrece una estrategia para utilizar la geometría CAD, en forma de parches NURBS, para tratar las intersecciones, como el ala-fuselaje. • No existen muchas alternativas de librerías NURBS viables. En este trabajo se ha desarrollado una librería, DOMINO NURBS, y se ofrece a la comunidad como código libre y abierto. • También se ha implementado un código CFD en tarjeta gráfica, para realizar una valoración de cómo se puede adaptar un código sobre malla no estructurada a arquitecturas paralelas. • Finalmente, se propone una metodología, basada en la función de Green, como una forma eficiente de paralelizar simulaciones numéricas. Esta tesis ha sido apoyada por las actividades realizadas por el Área de Dinámica da Fluidos del Instituto Nacional de Técnica Aeroespacial (INTA), a través de numerosos proyectos de financiación nacional: DOMINO, SIMUMAT, y CORESFMULAERO. También ha estado en consonancia con las actividades realizadas por el departamento de Métodos y Herramientas de Airbus España y con el grupo Investigación y Tecnología Aeronáutica Europeo (GARTEUR), AG/52. ABSTRACT The motivation of this work is the development of an automatic optimization strategy for large scale shape optimization problems that arise in the aeronautics industry to improve the aerodynamic performance; covering several aspects from the use of Non-Uniform Rational B-Splines (NURBS), the calculation of the gradients with the continuous adjoint formulation, the development of volumetric b-splines parameterization, mesh adaptation and intersection handling, to the adaptation of Computational Fluid Dynamics (CFD) algorithms to take advantage of highly parallel architectures in order to speed up the optimization process. With the development of the adjoint formulation, gradient-based methods for aerodynamic optimization become a promising approach to improve the aerodynamic performance of aircraft designs. The adjoint methodology allows the evaluation the gradients to all design variables of a cost function, such as drag or lift, at the equivalent cost of more or less one CFD simulation. However, some practical problems have been delaying its full implementation to the industry, which can be summarized as: integrability, computer performance, and adjoint robustness. This work tackles some of these issues and analyse them in well-known test cases. As summary, the contributions comprises: • The employment of NURBS as design variables in an automatic optimization loop for the improvement of the aerodynamic performance of aircraft wings in transonic regimen. • The development of point inversion algorithms to calculate the NURBS parametric coordinates from the space coordinates, to link with the computational grid vertex. • The use and validation of the adjoint formulation to calculate the gradients from the surface sensitivities in an automatic optimization loop and evaluate its reliability, compared with finite differences. • This work proposes some algorithms that take advantage of the underlying CAD geometry description, in the form of NURBS patches, to handle intersections and mesh adaptations. • There are not many usable libraries for NURBS available. In this work an open source library DOMINO NURBS has been developed and is offered to the community as free, open source code. • The implementation of a transonic CFD solver from scratch in a graphic card, for an assessment of the implementability of conventional CFD solvers for unstructured grids to highly parallel architectures. • Finally, this research proposes the use of the Green's function as an efficient paralellization scheme of numerical solvers. The presented work has been supported by the activities carried out at the Fluid Dynamics branch of the National Institute for Aerospace Technology (INTA) through national founding research projects: DOMINO, SIMUMAT, and CORESIMULAERO; in line with the activities carried out by the Methods and Tools and Flight Physics department at Airbus and the Group for Aeronautical Research and Technology in Europe (GARTEUR) action group AG/52.

Fatiga en CFRP: Caracterización y Método Óptico para la Estimación del Daño

El desarrollo de nuevas estructuras aeroespaciales optimizadas, utilizan materiales compuestos, para los componentes críticos y subsistemas, principalmente polímeros reforzados con fibra de carbono (CFRP). Un conocimiento profundo del estado de daño por fatiga de estructuras de CFRP avanzado, es esencial para predecir la vida residual y optimizar los intervalos de inspección estructural, reparaciones y/o sustitución de componentes. Las técnicas actuales se basan principalmente en la medición de cargas estructurales a lo largo de la vida útil de la estructura mediante galgas extensométricas eléctricas. Con esos datos, se estima la vida a fatiga utilizando modelos de acumulación de daño. En la presente tesis, se evalúa la metodología convencional para la estimación de la vida a fatiga de un CFRP aeronáutico. Esta metodología está basada en la regla de acumulación de daño lineal de Palmgren-Miner, y es aplicada para determinar la vida a fatiga de estructuras sometidas a cargas de amplitud variable. Se ha realizado una campaña de ensayos con cargas de amplitud constante para caracterizar un CFRP aeronáutico a fatiga, obteniendo las curvas clásicas S-N, en diferentes relaciones de esfuerzo. Se determinaron los diagramas de vida constante, (CLD), también conocidos como diagramas de Goodman, utilizando redes neuronales artificiales debido a la ausencia de modelos coherentes para materiales compuestos. Se ha caracterizado la degradación de la rigidez debido al daño por fatiga. Se ha ensayado un segundo grupo de probetas con secuencias estandarizadas de cargas de amplitud variable, para obtener la vida a fatiga y la degradación de rigidez en condiciones realistas. Las cargas aplicadas son representativas de misiones de aviones de combate (Falstaff), y de aviones de transporte (Twist). La vida a fatiga de las probetas cicladas con cargas de amplitud variable, se comparó con el índice de daño teórico calculado en base a la regla de acumulación de daño lineal convencional. Los resultados obtenidos muestran predicciones no conservativas. Esta tesis también presenta el estudio y desarrollo, de una nueva técnica de no contacto para evaluar el estado de daño por fatiga de estructuras de CFRP por medio de cambios de los parámetros de rugosidad. La rugosidad superficial se puede medir fácilmente en campo con métodos sin contacto, mediante técnicas ópticas tales como speckle y perfilómetros ópticos. En el presente estudio, se han medido parámetros de rugosidad superficial, y el factor de irregularidad de la superficie, a lo largo de la vida de las probetas cicladas con cargas de amplitud constante y variable, Se ha obtenido una buena tendencia de ajuste al correlacionar la magnitud de la rugosidad y el factor de irregularidad de la superficie con la degradación de la rigidez de las probetas fatigadas. Estos resultados sugieren que los cambios en la rugosidad superficial medida en zonas estratégicas de componentes y estructuras hechas de CFRP, podrían ser indicativas del nivel de daño interno debido a cargas de fatiga. Los resultados también sugieren que el método es independiente del tipo de carga de fatiga que ha causado el daño. Esto último hace que esta técnica de medición sea aplicable como inspección para una amplia gama de estructuras de materiales compuestos, desde tanques presurizados con cargas de amplitud constante, estructuras aeronáuticas como alas y colas de aeronaves cicladas con cargas de amplitud variable, hasta aplicaciones industriales como automoción, entre otros. ABSTRACT New optimized aerospace structures use composite materials, mainly carbon fiber reinforced polymer composite (CFRP), for critical components and subsystems. A strong knowledge of the fatigue state of highly advanced (CFRP) structures is essential to predict the residual life and optimize intervals of structural inspection, repairs, and/or replacements. Current techniques are based mostly on measurement of structural loads throughout the service life by electric strain gauge sensors. These sensors are affected by extreme environmental conditions and by fatigue loads in such a way that the sensors and their systems require exhaustive maintenance throughout system life. In the present thesis, the conventional methodology based on linear damage accumulation rules, applied to determine the fatigue life of structures subjected to variable amplitude loads was evaluated for an aeronautical CFRP. A test program with constant amplitude loads has been performed to obtain the classical S-N curves at different stress ratios. Constant life diagrams, CLDs, where determined by means of Artificial Neural Networks due to the absence of consistent models for composites. The stiffness degradation due to fatigue damage has been characterized for coupons under cyclic tensile loads. A second group of coupons have been tested until failure with a standardized sequence of variable amplitude loads, representative of missions for combat aircraft (Falstaff), and representative of commercial flights (Twist), to obtain the fatigue life and the stiffness degradation under realistic conditions. The fatigue life of the coupons cycled with variable amplitude loads were compared to the theoretical damage index calculated based on the conventional linear damage accumulation rule. The obtained results show non-conservative predictions. This thesis also presents the evaluation of a new non-contact technique to evaluate the fatigue damage state of CFRP structures by means of measuring roughness parameters to evaluate changes in the surface topography. Surface roughness can be measured easily on field with non-contact methods by optical techniques such as speckle and optical perfilometers. In the present study, surface roughness parameters, and the surface irregularity factor, have been measured along the life of the coupons cycled with constant and variable amplitude loads of different magnitude. A good agreement has been obtained when correlating the magnitude of the roughness and the surface irregularity factor with the stiffness degradation. These results suggest that the changes on the surface roughness measured in strategic zones of components and structures made of CFRP, could be indicative of the level of internal damage due to fatigue loads. The results also suggest that the method is independent of the type of fatigue load that have caused the damage. It makes this measurement technique applicable for a wide range of inspections of composite materials structures, from pressurized tanks with constant amplitude loads, to variable amplitude loaded aeronautical structures like wings and empennages, up to automotive and other industrial applications.

Hidrodinamica de planeadores submarinos y su impacto en la funcionalidad de sensores CTD

Los recientes desarrollos tecnológicos permiten la transición de la oceanografía observacional desde un concepto basado en buques a uno basado en sistemas autónomos en red. Este último, propone que la forma más eficiente y efectiva de observar el océano es con una red de plataformas autónomas distribuidas espacialmente y complementadas con sistemas de medición remota. Debido a su maniobrabilidad y autonomía, los planeadores submarinos están jugando un papel relevante en este concepto de observaciones en red. Los planeadores submarinos fueron específicamente diseñados para muestrear vastas zonas del océano. Estos son robots con forma de torpedo que hacen uso de su forma hidrodinámica, alas y cambios de flotabilidad para generar movimientos horizontales y verticales en la columna de agua. Un sensor que mide conductividad, temperatura y profundidad (CTD) constituye un equipamiento estándar en la plataforma. Esto se debe a que ciertas variables dinámicas del Océano se pueden derivar de la temperatura, profundidad y salinidad. Esta última se puede estimar a partir de las medidas de temperatura y conductividad. La integración de sensores CTD en planeadores submarinos no esta exenta de desafíos. Uno de ellos está relacionado con la precisión de los valores de salinidad derivados de las muestras de temperatura y conductividad. Específicamente, las estimaciones de salinidad están significativamente degradadas por el retardo térmico existente, entre la temperatura medida y la temperatura real dentro de la celda de conductividad del sensor. Esta deficiencia depende de las particularidades del flujo de entrada al sensor, su geometría y, también se ha postulado, del calor acumulado en las capas de aislamiento externo del sensor. Los efectos del retardo térmico se suelen mitigar mediante el control del flujo de entrada al sensor. Esto se obtiene generalmente mediante el bombeo de agua a través del sensor o manteniendo constante y conocida su velocidad. Aunque recientemente se han incorporado sistemas de bombeo en los CTDs a bordo de los planeadores submarinos, todavía existen plataformas equipadas con CTDs sin dichos sistemas. En estos casos, la estimación de la salinidad supone condiciones de flujo de entrada al sensor, razonablemente controladas e imperturbadas. Esta Tesis investiga el impacto, si existe, que la hidrodinámica de los planeadores submarinos pudiera tener en la eficiencia de los sensores CTD. Específicamente, se investiga primero la localización del sensor CTD (externo al fuselaje) relativa a la capa límite desarrollada a lo largo del cuerpo del planeador. Esto se lleva a cabo mediante la utilización de un modelo acoplado de fluido no viscoso con un modelo de capa límite implementado por el autor, así como mediante un programa comercial de dinámica de fluidos computacional (CFD). Los resultados indican, en ambos casos, que el sensor CTD se encuentra fuera de la capa límite, siendo las condiciones del flujo de entrada las mismas que las del flujo sin perturbar. Todavía, la velocidad del flujo de entrada al sensor CTD es la velocidad de la plataforma, la cual depende de su hidrodinámica. Por tal motivo, la investigación se ha extendido para averiguar el efecto que la velocidad de la plataforma tiene en la eficiencia del sensor CTD. Con este propósito, se ha desarrollado un modelo en elementos finitos del comportamiento hidrodinámico y térmico del flujo dentro del CTD. Los resultados numéricos indican que el retardo térmico, atribuidos originalmente a la acumulación de calor en la estructura del sensor, se debe fundamentalmente a la interacción del flujo que atraviesa la celda de conductividad con la geometría interna de la misma. Esta interacción es distinta a distintas velocidades del planeador submarino. Específicamente, a velocidades bajas del planeador (0.2 m/s), la mezcla del flujo entrante con las masas de agua remanentes en el interior de la celda, se ralentiza debido a la generación de remolinos. Se obtienen entonces desviaciones significantes entre la salinidad real y aquella estimada. En cambio, a velocidades más altas del planeador (0.4 m/s) los procesos de mezcla se incrementan debido a la turbulencia e inestabilidades. En consecuencia, la respuesta del sensor CTD es mas rápida y las estimaciones de la salinidad mas precisas que en el caso anterior. Para completar el trabajo, los resultados numéricos se han validado con pruebas experimentales. Específicamente, se ha construido un modelo a escala del sensor CTD para obtener la confirmación experimental de los modelos numéricos. Haciendo uso del principio de similaridad de la dinámica que gobierna los fluidos incompresibles, los experimentos se han realizado con flujos de aire. Esto simplifica significativamente la puesta experimental y facilita su realización en condiciones con medios limitados. Las pruebas experimentales han confirmado cualitativamente los resultados numéricos. Más aun, se sugiere en esta Tesis que la respuesta del sensor CTD mejoraría significativamente añadiendo un generador de turbulencia en localizaciones adecuadas al interno de la celda de conductividad. ABSTRACT Recent technological developments allow the transition of observational oceanography from a ship-based to a networking concept. The latter suggests that the most efficient and effective way to observe the Ocean is through a fleet of spatially distributed autonomous platforms complemented by remote sensing. Due to their maneuverability, autonomy and endurance at sea, underwater gliders are already playing a significant role in this networking observational approach. Underwater gliders were specifically designed to sample vast areas of the Ocean. These are robots with a torpedo shape that make use of their hydrodynamic shape, wings and buoyancy changes to induce horizontal and vertical motions through the water column. A sensor to measure the conductivity, temperature and depth (CTD) is a standard payload of this platform. This is because certain ocean dynamic variables can be derived from temperature, depth and salinity. The latter can be inferred from measurements of temperature and conductivity. Integrating CTD sensors in glider platforms is not exempted of challenges. One of them, concerns to the accuracy of the salinity values derived from the sampled conductivity and temperature. Specifically, salinity estimates are significantly degraded by the thermal lag response existing between the measured temperature and the real temperature inside the conductivity cell of the sensor. This deficiency depends on the particularities of the inflow to the sensor, its geometry and, it has also been hypothesized, on the heat accumulated by the sensor coating layers. The effects of thermal lag are usually mitigated by controlling the inflow conditions through the sensor. Controlling inflow conditions is usually achieved by pumping the water through the sensor or by keeping constant and known its diving speed. Although pumping systems have been recently implemented in CTD sensors on board gliders, there are still platforms with unpumped CTDs. In the latter case, salinity estimates rely on assuming reasonable controlled and unperturbed flow conditions at the CTD sensor. This Thesis investigates the impact, if any, that glider hydrodynamics may have on the performance of onboard CTDs. Specifically, the location of the CTD sensor (external to the hull) relative to the boundary layer developed along the glider fuselage, is first investigated. This is done, initially, by applying a coupled inviscid-boundary layer model developed by the author, and later by using a commercial software for computational fluid dynamics (CFD). Results indicate, in both cases, that the CTD sensor is out of the boundary layer, being its inflow conditions those of the free stream. Still, the inflow speed to the CTD sensor is the speed of the platform, which largely depends on its hydrodynamic setup. For this reason, the research has been further extended to investigate the effect of the platform speed on the performance of the CTD sensor. A finite element model of the hydrodynamic and thermal behavior of the flow inside the CTD sensor, is developed for this purpose. Numerical results suggest that the thermal lag effect is mostly due to the interaction of the flow through the conductivity cell and its geometry. This interaction is different at different speeds of the glider. Specifically, at low glider speeds (0.2 m/s), the mixing of recent and old waters inside the conductivity cell is slowed down by the generation of coherent eddy structures. Significant departures between real and estimated values of the salinity are found. Instead, mixing is enhanced by turbulence and instabilities for high glider speeds (0.4 m/s). As a result, the thermal response of the CTD sensor is faster and the salinity estimates more accurate than for the low speed case. For completeness, numerical results have been validated against model tests. Specifically, a scaled model of the CTD sensor was built to obtain experimental confirmation of the numerical results. Making use of the similarity principle of the dynamics governing incompressible fluids, experiments are carried out with air flows. This significantly simplifies the experimental setup and facilitates its realization in a limited resource condition. Model tests qualitatively confirm the numerical findings. Moreover, it is suggested in this Thesis that the response of the CTD sensor would be significantly improved by adding small turbulators at adequate locations inside the conductivity cell.

O PROTESTANTISMO BRASILEIRO: ENTRE A COLABORAÇÃO E A RESISTÊNCIA NO PERÍODO DA DI-TADURA CIVIL E MILITAR (1964-1974)

Este trabalho analisa um período de crise vivido pelo protestantismo brasileiro (simbolizado aqui pela Igreja Metodista e pela Igreja Presbiteriana do Brasil) durante a época da Ditadura Civil e Militar, focando o olhar mais especificamente no intervalo entre os anos de 1964 e 1974. Influenciadas pelo ambiente político e ideológico da época, essas duas denominações protestantes foram palco de uma disputa entre suas alas conservadoras e progressistas. Como resultado, estabeleceu-se um clima interno de “caça às bruxas”, marcado por atitudes autoritá-rias e de apoio ao regime imposto. Seguindo uma proposta advinda de trabalhos anteriores, a pesquisa procura levantar os fundamentos que embasaram as atitudes das alas conservadoras do protestantismo nesse conflito, um aspecto pouco considerado pela historiografia sobre o tema. A principal suspeita é a de que as posturas conservadoras decorreram do contato do pro-testantismo importado do mundo anglo saxão com a herança cultural patriarcal autoritária e católica presente no Brasil desde seu período fundacional. Essa mescla de elementos teológi-cos importados somada à herança cultural tipicamente brasileira acabou moldando a mentali-dade dos setores conservadores do protestantismo nacional entre o final do século XIX e me-ados do XX, que acabou aflorando quando novos agentes surgiram no cenário religioso duran-te o período do Golpe Civil e Militar.

Proximo–distal specification in the wing disc of Drosophila by the nubbin gene

Mutations in the nubbin (nub) gene have a phenotype consisting of a severe wing size reduction and pattern alterations, such as transformations of distal elements into proximal ones. nub expression is restricted to the wing pouch cells in wing discs since early larval development. These effects are also observed in genetic mosaics where cell proliferation is reduced in all wing blade regions autonomously, and transformation into proximal elements is observed in distal clones. Clones located in the proximal region of the wing blade cause in addition nonautonomous reduction of the whole wing. Cell lineage experiments in a nub mutant background show that clones respect neither the anterior–posterior nor the dorsal–ventral boundary but that the selector genes have been correctly expressed since early larval development. The phenotypes of nub el and nub dpp genetic combinations are synergistic and the overexpression of dpp in clones in nub wings does not result in overproliferation of the surrounding wild-type cells. We discuss the role of nub in the wing’s proximo–distal axis and in the formation of compartment boundaries.

Molecular phylogenetic analysis of evolutionary trends in stonefly wing structure and locomotor behavior

Insects in the order Plecoptera (stoneflies) use a form of two-dimensional aerodynamic locomotion called surface skimming to move across water surfaces. Because their weight is supported by water, skimmers can achieve effective aerodynamic locomotion even with small wings and weak flight muscles. These mechanical features stimulated the hypothesis that surface skimming may have been an intermediate stage in the evolution of insect flight, which has perhaps been retained in certain modern stoneflies. Here we present a phylogeny of Plecoptera based on nucleotide sequence data from the small subunit rRNA (18S) gene. By mapping locomotor behavior and wing structural data onto the phylogeny, we distinguish between the competing hypotheses that skimming is a retained ancestral trait or, alternatively, a relatively recent loss of flight. Our results show that basal stoneflies are surface skimmers, and that various forms of surface skimming are distributed widely across the plecopteran phylogeny. Stonefly wings show evolutionary trends in the number of cross veins and the thickness of the cuticle of the longitudinal veins that are consistent with elaboration and diversification of flight-related traits. These data support the hypothesis that the first stoneflies were surface skimmers, and that wing structures important for aerial flight have become elaborated and more diverse during the radiation of modern stoneflies.

Arthropods: Developmental diversity within a (super) phylum

The expression patterns of developmental genes provide new markers that address the homology of body parts and provide clues as to how body plans have evolved. Such markers support the idea that insect wings evolved from limbs but refute the idea that insect and crustacean jaws are fundamentally different in structure. They also confirm that arthropod tagmosis reflects underlying patterns of Hox gene regulation but they do not yet resolve to what extent Hox expression domains may serve to define segment homologies.

Cell cycling and patterned cell proliferation in the Drosophila wing during metamorphosis.

In metamorphosing wing discs, progression through the cell cycle takes place, as in larval discs, in nonclonally derived clusters of cells synchronized in the same cell cycle stage. Contrary to early discs, there are temporal and spatial heterogeneities in cell proliferation associated with wing margin, vein, intervein, and middle intervein territories. Within these territories, there are no indications of a wave progression of the cell cycle. Mitotic orientations are, as in early discs, at random but there is a preferential allocation of postmitotic cells along the proximodistal axis, thus explaining the elongated shape of the resulting clones along this axis. Shapes of clones in mature discs and in evaginated wings are similar, thus excluding major morphogenetic movements during evagination. After the proliferative period, all the cells are arrested in G1 phase. The final number of cells of the wing is fixed independently of experimental perturbations that alter the cell division schedule. These results are discussed in the context of a model of wing morphogenesis.

Estabelecimento e desenvolvimento de mudas pré-brotadas de cana-de-açúcar sob diferentes lâminas de irrigação

Na atual conjuntura, no que se refere à energia renovável, o etanol é um dos principais, se não o mais importante, produto brasileiro. Proveniente da fermentação de açúcares, processo conhecido há séculos, tem se tornado o carro chefe do país como garantia de voz ativa nas discussões energéticas pelo mundo afora. Porém, atualmente, o setor sucroalcooleiro está passando por um momento de cautela devido à queda de produtividade e longevidade dos canaviais ao longo dos últimos anos ocasionados principalmente pela mecanização da colheita e plantio da cana-de-açúcar. Cabe ressaltar que as perdas de produção podem ser ainda maiores diante da ausência do manejo varietal e de cuidados adequados em relação à sanidade de mudas utilizadas para a multiplicação de viveiros. Nesse sentido, nos últimos anos, o emprego da irrigação no cultivo da cana-de-açúcar associada a outras tecnologias de plantio, tais como formação de viveiros com mudas pré-brotadas, vem merecendo papel de destaque. Esse cenário obriga pesquisadores a buscar novas tecnologias para aumento de produtividade, longevidade dos canaviais e redução do custo por tonelada de cana produzida, tais como a produção de mudas sadias para formação de viveiros de cana-de-açúcar. Diante disso, a presente pesquisa teve por objetivo, submeter mudas pré-brotadas de cana-de-açúcar, durante plantio de inverno, na região de Piracicaba, SP, sob diferentes lâminas de irrigação (10 mm; 20 mm; 30 mm e 40 mm), utilizando um sistema de irrigação por aspersão com alas móveis. Dessa forma, buscou-se determinar qual seria a melhor lâmina de irrigação, necessária para garantir o melhor índice de pegamento e alto vigor no estabelecimento e desenvolvimento das mudas pré-brotadas de cana-de-açúcar para a região de Piracicaba-SP. Foram feitas avaliações periódicas (não destrutivas), tais como: mortalidade das mudas; clorofila total na folha; tamanho da muda; índice de área foliar; número de perfilhos brotados por metro; percentual de falha no canavial. Além de avaliações periódicas (destrutivas), tais como: avaliação do tamanho da raiz; massa seca da raiz; massa seca da parte aérea e número de perfilhos totais. As análises estatísticas das lâminas de irrigação foram realizadas pelo método de Tukey ao nível de 5% de probabilidade. Diante dos resultados obtidos, verificou-se que a lâmina de 10 mm possibilitou os melhores índices de pegamento e proporcionou um índice superior a 97,8% de sobrevivência de mudas. Também, observou-se uma estreita relação entre o índice de mortalidade no plantio de inverno das mudas pré-brotadas de cana-de-açúcar com o manejo da irrigação, a qual nos primeiros dias após plantio foi fundamental para o estabelecimento e desenvolvimento das mudas. Cabe ressaltar que em caso da adoção de outro manejo de irrigação, com lâminas maiores, nessas condições experimentais, possivelmente haveria perdas de água, cujo fato nos dias atuais não é o ideal tendo em vista a busca por economia e manejo racional da água.

Optical and ultraviolet observations of a strong flare in the young, single K2 dwarf LQ Hya

We present high-resolution optical echelle spectra and IUE observations during a strong flare on 1993 December 22 in the very active, young, rapidly rotating, single K2 dwarf LQ Hya. The initial impulsive phase of the flare, which started sometime between 2:42 ut and 4:07 ut, was characterized by strong optical continuum enhancement and blueshifted emission lines with broad wings. The optical chromospheric lines reached their maximum intensity at ≈ 5:31 ut, by which time the blueshift vanished and the optical continuum enhancement had sharply decreased. Thereafter, the line emission slowly decreased and the lines redshift in a gradual phase that lasted at least two more hours. The Mg II lines behaved similarly. Quiescent C IV flux levels were not recovered until 21 h later, though a data gap and a possible second flare make the interpretation uncertain. In addition to the typically flare-enhanced emission lines (e.g., H α and H β), we observe He I D_3 going into emission, plus excess emission (after subtraction of the quiescent spectrum) in other He I and several strong neutral metal lines (e.g., Mg I b). Flare enhancement of the far-ultraviolet continuum generally agrees with an Si I recombination model. We estimate the total flare energy, and discuss the broad components, asymmetries and Doppler shifts seen in some of the emission lines.

Water polo throwing speed and body composition: an analysis by playing positions and opposition level

The aim of this study was to develop an anthropometric profile on highly skilled male water polo players by specific playing positions. Also, to identify significant relationships between these features an overhead throwing speed in highly skilled male Water Polo players by specific playing positions. Methods: A total of 94 male water polo players (24.5±5.3 yrs) who were playing in the Spanish King´s cup were studied. Subjects were grouped according to their specific playing positions: 15 goalkeepers, 45 offensive wings, 20 center backs and 14 center forwards. Anthropometric assessment was made following ISAK protocols. Hand grip and throwing speed in several situations were also assessed. A one-way analysis of variance (ANOVA) was used to determine if significant differences existed among the four playing positions. Pearson product-moment correlation coefficients (r) were used to determine the relationships of all anthropometric measures with throwing speed and hand grip. The total player’s somatotype was endomorphic-mesomorphic (2.9–5.8–2.3). Center forwards exhibit important anthropometric differences compared with the other specific playing positions in elite male water polo players, but no differences were found in throwing speed by specific playing positions in each throwing conditions. Moreover, a higher number of relationships between anthropometric and throwing speed were found in wings and also in center backs but no relationships were found in center forwards. The data reflects the importance of muscle mass and upper body in the throwing skill. Coaches can use this information in order to select players for the different specific positions.