Laminar flow of a gas in a tube with large temperature differences.

The laminar low Mach number flow of a gas in a tube is analyzed for very small and very large values of the inlet-to-wall temperature ratio. When this ratio tends to zero, pressure forces confine the cold gas to a thin core around the axis of the tube. This core is neatly bounded by an ablation front that consumes it at a finite distance from the tube inlet. When the temperature ratio tends to infinity, the temperature of the gas increases smoothly from the wall to the axis of the tube and the shear stress and heat flux are positive at the wall despite the fact that the viscosity and thermal conductivity of the gas scaled with their inlet values tend to zero at the wall

Linear global instability of non-orthogonal incompressible swept attachment-line boundary layer flow

Instability of the orthogonal swept attachment line boundary layer has received attention by local1, 2 and global3–5 analysis methods over several decades, owing to the significance of this model to transition to turbulence on the surface of swept wings. However, substantially less attention has been paid to the problem of laminar flow instability in the non-orthogonal swept attachment-line boundary layer; only a local analysis framework has been employed to-date.6 The present contribution addresses this issue from a linear global (BiGlobal) instability analysis point of view in the incompressible regime. Direct numerical simulations have also been performed in order to verify the analysis results and unravel the limits of validity of the Dorrepaal basic flow7 model analyzed. Cross-validated results document the effect of the angle _ on the critical conditions identified by Hall et al.1 and show linear destabilization of the flow with decreasing AoA, up to a limit at which the assumptions of the Dorrepaal model become questionable. Finally, a simple extension of the extended G¨ortler-H¨ammerlin ODE-based polynomial model proposed by Theofilis et al.4 is presented for the non-orthogonal flow. In this model, the symmetries of the three-dimensional disturbances are broken by the non-orthogonal flow conditions. Temporal and spatial one-dimensional linear eigenvalue codes were developed, obtaining consistent results with BiGlobal stability analysis and DNS. Beyond the computational advantages presented by the ODE-based model, it allows us to understand the functional dependence of the three-dimensional disturbances in the non-orthogonal case as well as their connections with the disturbances of the orthogonal stability problem.

Laminar counterflow parallel-plate heat exchangers: Exact and approximate solutions

Multilayered, counterflow, parallel-plate heat exchangers are analyzed numerically and theoretically. The analysis, carried out for constant property fluids, considers a hydrodynamically developed laminar flow and neglects longitudinal conduction both in the fluid and in the plates. The solution for the temperature field involves eigenfunction expansions that can be solved in terms of Whittaker functions using standard symbolic algebra packages, leading to analytical expressions that provide the eigenvalues numerically. It is seen that the approximate solution obtained by retaining the first two modes in the eigenfunction expansion provides an accurate representation for the temperature away from the entrance regions, specially for long heat exchangers, thereby enabling simplified expressions for the wall and bulk temperatures, local heat-transfer rate, overall heat-transfer coefficient, and outlet bulk temperatures. The agreement between the numerical and theoretical results suggests the possibility of using the analytical solutions presented herein as benchmark problems for computational heat-transfer codes.

Flujo laminar: el cementerio de Igualada y los procesos elásticos en la arquitectura de Enric Miralles y Carme Pinós

La tesis Flujo Laminar, El cementerio de Igualada y los procesos elásticos en la arquitectura de Enric Miralles y Carme Pinós analiza la metodología que utilizan y desarrollan los arquitectos Miralles y Pinós en el proyecto del cementerio de Igualada. Enric Miralles y Carme Pinós comienzan a trabajar juntos en 1983, separándose siete años después. La producción arquitectónica que generan durante este periodo ha sido valorada y considerada por la crítica como una de las de mayor calidad en el último cuarto del siglo XX. Respecto a esta etapa de colaboración existen artículos dispersos que analizan de manera aislada algunos aspectos de sus proyectos. Sin embargo, no se han realizado estudios que analicen su metodología proyectual, sus herramientas, sus estrategias y sus diferentes conexiones y referencias. Tampoco se han analizado hasta el momento, cómo son sus procesos proyectuales, sus tiempos y sus objetivos. En este sentido, el proyecto del cementerio de Igualada será clave en la trayectoria del equipo. El tiempo extenso empleado en el proceso y la singularidad de la obra, además de otros factores del propio imaginario de Miralles y Pinós, marcarán a este proyecto como un punto de inflexión en su trabajo. La investigación plantea, en primer lugar, la descripción del contexto en el cual se comienzan a desarrollar los proyectos iniciales de Miralles y Pinós, además de los antecedentes que generarán la propuesta para el cementerio de Igualada. Seguidamente, se describen y analizan los apoyos y las referencias que los arquitectos utilizan en este proyecto, tanto las vinculadas a la cultura local como las atrapadas desde el imaginario universal. Por otro lado, el bloque central de la investigación aporta doce herramientas que construyen la metodología proyectual de Miralles y Pinós. Esta contribución se ha realizado desde el análisis y el cruce de los documentos originales del proyecto de Igualada y los escritos existentes de los arquitectos. Las herramientas aportadas son: deslizar, desplazar, repetir, enterrar, constreñir, oscilar, estirar, desenredar, desviar, rehacer, hendir y fluir. Todas ellas se describen, analizan e interpretan desde setenta y dos documentos esenciales extraídos del proceso de Igualada. Un último capítulo de conclusiones, define lo que se presenta en la investigación como una metodología propia de Enric Miralles y Carme Pinós, denominada procesos elásticos, en el que se describen sus cualidades y sus tiempos, a la vez que se presenta también una táctica empleada en el proyecto de Igualada denominada flujo laminar. ABSTRACT The thesis Laminar Flow, the Igualada cemetery and the elastic processes in the architecture of Enric Miralles and Carme Pinós analyses the methodology that the architects Miralles and Pinós used in the project for the Igualada cemetery park. Enric Miralles and Carme Pinós began to work together in 1983, and went their different ways seven years later. The architectural production they generated during that period has been valued and considered by critics to be among the greatest quality of production in the final quarter of the twentieth century. There is a scattering of articles about this period which give an independent analysis of some features of their products. However, there are no studies which analyse their project design methodology, their tools, their strategies and their different connections and references. Neither has there been analysis to date of the nature of their project design processes, nor of their times and their aims. Within this context, the Igualada cemetery project was key in the path to be trodden by the team. The great length of time used on the process and the singularity of the work, alongside other factors from Miralles and Pinós's personal imaginarium, were to mark this project as a turning point in their work. This research sets out, first of all, to describe the context in which the early projects by Miralles and Pinós began to be developed, as well as the background to the generation of their proposal for the Igualada cemetery. There follows a description and analysis of the resources and of the references that the architects used in this project, both those linked to local culture and those picked from the universal imaginarium. Furthermore, the central block of the research identifies twelve tools which make up Miralles and Pinós's project design methodology. This contribution has been performed on the basis of analysis and comparison of the original Igualada project documents and of writings extant by the architects. The tools identified are: slide, shift, repeat, bury, constrain, oscillate, stretch, untangle, divert, redo, groove and flow. They are all described, analysed and interpreted on the basis of seventy-two essential documents extracted from the Igualada process. A final chapter of conclusions defines what is presented in the research as a methodology which is specific to Enric Miralles and Carme Pinós, denominated elastic processes, describing their qualities and their times, along with the presentation of a tactic used in the Igualada project which is denominated laminar flow.

Validación del método de predicción de direcciones principales de drenaje subterráneo en macizos anisótropos, en los terrenos volcánicos del macizo de Anaga, Tenerife

Actualmente y desde hace ya más de 25 años, el Método de “Predicción de las Direcciones Principales de Drenaje Subterráneo en Macizos Anisótropos”, ha sido utilizado con éxito en diferentes terrenos Kársticos como: calizas, yesos, cuarcitas, pizarras, granitos y criokarst (karst en el hielo glaciar). Sin embargo hasta ahora, nunca se había validado en terrenos volcánicos donde está focalizada esta tesis que lleva por título, Validación de dicho Método en los Terrenos Volcánicos del Macizo de Anaga en Tenerife. Este Método matemático consiste esencialmente en “Predecir y Cuantificar” las direcciones principales de drenaje turbulento subterráneo en macizos anisótropos. Para ello se basa en el estudio realizado en campo de los tectoglifos o deformaciones permanentes del macizo, impresas éstas en la roca, como consecuencia de los esfuerzos tectónicos a los que ha estado sometido dicho macizo. Se consigue de esta manera cubrir el vacío para macizos anisótropos que existe con el modelo matemático de flujo subterráneo laminar (macizos isótropos) definido por Darcy (1856). Para validar el Método se ha elegido el macizo de Anaga, pues es la zona de mayor anisotropía existente en la isla de Tenerife, conformada por una gran y extensa red de diques de diversas formas y tamaños que pertenecen a la familia de diques del eje estructural NE de la isla. En dicho macizo se realizó un exhaustivo trabajo de campo con la toma 331 datos (diques basálticos) y se aplicó el Método, consiguiendo definir las direcciones preferentes de drenaje subterráneo en el macizo de Anaga. Esta predicción obtenida se contrastó con la realidad del drenaje en la zona, conocida gracias a la existencia de cinco galerías ubicadas en la zona trabajo, de las cuales se tiene información sobre sus alumbramientos. En todos los casos se demuestra la bondad de la predicción obtenida con el Método. Queda demostrado que a mayor caos geológico o geotectónico, se ha conseguido mejor predicción del Método, obteniéndose resultados muy satisfactorios para aquellas galerías de agua en las que su rumbo de avance fue coincidente con la dirección perpendicular a la obtenida con la predicción dada por el Método, como dirección preferente de drenaje en la zona en la que se encuentra ubicada cada galería. No cabe duda que la validación de Método en los terrenos volcánicos de Tenerife, supondrá un cambio considerable en el mundo de la hidrogeología en este tipo de terrenos. Es la única herramienta matemática que se dispone para predecir un rumbo acertado en el avance de la perforación de las galerías de aguas, lo que conlleva al mismo tiempo un ahorro importantísimo en la ejecución de las obras. Por otro lado, el Método deja un importante legado a la sociedad canaria, pues con él se abren numerosas vías de trabajo e investigación que generarán un importante desarrollo en el mundo de la hidrogeología volcánica. ABSTRACT Currently and for over 25 years now, the Method of "Prediction of Subsurface Drainage Main Directions in Anisotropic Massifs" has been successfully used in various karstic terrains such as: limestone, gypsum, quartzite, slate, granite and criokarst (karst in the glacier ice). However, until now, it had never been validated in volcanic terrains where is focused this thesis entitled Validation of such Method in the Anaga Massif Volcanic Terrains, in Tenerife. This mathematical method is essentially "predict and quantify" the main directions of groundwater turbulent drainage in anisotropic massifs. This is based on field study of tectoglifes or permanent deformation of the massif, printed on the rocks as a result of previous tectonic stresses. Therefore it is possible to use in anisotropic rock mathematical model instead of the isotropic laminar flow mathematical models defined by Darcy (1856). The Anaga Massif have been chosen to validate the method, because it presents the greatest anisotropy in Tenerife Island, shaped by a large and extensive network of dikes of various shapes and sizes that belong to the family of NE structural axis dikes of the island. An exhaustive field work was carried out in such massif, with 331 collected data (basaltic dikes) and the method was applied, in order to define the preferred direction of the underground drainage in the Anaga massif. This obtained prediction was contrasted to the reality of the drainage in the area, known thanks to the existence of five galleries located in the work area, from which information about their springs was available. In all cases it was possible to demonstrate the fitness of the prediction obtained by the method. It had been demonstrated that a greater geological or geotectonic chaos enhances a better prediction of the method, that predicted very satisfactory results for those water galleries which directions were perpendicular to that predicted by the Method as a drainage preferential direction, for the zone where was located each gallery. No doubt that the validation of the use of the Method in the volcanic terrain of Tenerife, means a considerable change in the world of hydrogeology in this type of terrain. It is the only mathematical tool available to predict a successful drilling direction in advancing water galleries, what also leads to major savings in execution of the drilling works. Furthermore, the method leaves an important legacy to the Canary Islands society, because it opens many lines of work and research to generate a significant development in the world of volcanic hydrogeology.

Direct and adjoint global stability analysis of turbulent transonic flows over a NACA0012 profile

In this work, various turbulent solutions of the two-dimensional (2D) and three-dimensional compressible Reynolds averaged Navier?Stokes equations are analyzed using global stability theory. This analysis is motivated by the onset of flow unsteadiness (Hopf bifurcation) for transonic buffet conditions where moderately high Reynolds numbers and compressible effects must be considered. The buffet phenomenon involves a complex interaction between the separated flow and a shock wave. The efficient numerical methodology presented in this paper predicts the critical parameters, namely, the angle of attack and Mach and Reynolds numbers beyond which the onset of flow unsteadiness appears. The geometry, a NACA0012 profile, and flow parameters selected reproduce situations of practical interest for aeronautical applications. The numerical computation is performed in three steps. First, a steady baseflow solution is obtained; second, the Jacobian matrix for the RANS equations based on a finite volume discretization is computed; and finally, the generalized eigenvalue problem is derived when the baseflow is linearly perturbed. The methodology is validated predicting the 2D Hopf bifurcation for a circular cylinder under laminar flow condition. This benchmark shows good agreement with the previous published computations and experimental data. In the transonic buffet case, the baseflow is computed using the Spalart?Allmaras turbulence model and represents a mean flow where the high frequency content and length scales of the order of the shear-layer thickness have been averaged. The lower frequency content is assumed to be decoupled from the high frequencies, thus allowing a stability analysis to be performed on the low frequency range. In addition, results of the corresponding adjoint problem and the sensitivity map are provided for the first time for the buffet problem. Finally, an extruded three-dimensional geometry of the NACA0012 airfoil, where all velocity components are considered, was also analyzed as a Triglobal stability case, and the outcoming results were compared to the previous 2D limited model, confirming that the buffet onset is well detected.

Tranversal motion and flow structure of fully nonlinear streaks in a laminar boundary layer

Typical streak computations present in the literature correspond to linear streaks or to small amplitude nonlinear streaks computed using DNS or nonlinear PSE. We use the Reduced Navier-Stokes (RNS) equations to compute the streamwise evolution of fully non-linear streaks with high amplitude in a laminar flat plate boundary layer. The RNS formulation provides Reynolds number independent solutions that are asymptotically exact in the limit $Re \gg 1$, it requires much less computational effort than DNS, and it does not have the consistency and convergence problems of the PSE. We present various streak computations to show that the flow configuration changes substantially when the amplitude of the streaks grows and the nonlinear effects come into play. The transversal motion (in the wall normal-streamwise plane) becomes more important and strongly distorts the streamwise velocity profiles, that end up being quite different from those of the linear case. We analyze in detail the resulting flow patterns for the nonlinearly saturated streaks and compare them with available experimental results.

Three-dimensional flow instability in a lid-driven isosceles triangular cavity

Linear three-dimensional modal instability of steady laminar two-dimensional states developing in a lid-driven cavity of isosceles triangular cross-section is investigated theoretically and experimentally for the case in which the equal sides form a rectangular corner. An asymmetric steady two-dimensional motion is driven by the steady motion of one of the equal sides. If the side moves away from the rectangular corner, a stationary three-dimensional instability is found. If the motion is directed towards the corner, the instability is oscillatory. The respective critical Reynolds numbers are identified both theoretically and experimentally. The neutral curves pertinent to the two configurations and the properties of the respective leading eigenmodes are documented and analogies to instabilities in rectangular lid-driven cavities are discussed.

Efficient numerical methods for global linear instability. Analysis and modeling of non-orthogonal swept attachment-line boundary layer flow

The aim of this thesis is to study the mechanisms of instability that occur in swept wings when the angle of attack increases. For this, a simplified model for the a simplified model for the non-orthogonal swept leading edge boundary layer has been used as well as different numerical techniques in order to solve the linear stability problem that describes the behavior of perturbations superposed upon this base flow. Two different approaches, matrix-free and matrix forming methods, have been validated using direct numerical simulations with spectral resolution. In this way, flow instability in the non-orthogonal swept attachment-line boundary layer is addressed in a linear analysis framework via the solution of the pertinent global (Bi-Global) PDE-based eigenvalue problem. Subsequently, a simple extension of the extended G¨ortler-H¨ammerlin ODEbased polynomial model proposed by Theofilis, Fedorov, Obrist & Dallmann (2003) for orthogonal flow, which includes previous models as particular cases and recovers global instability analysis results, is presented for non-orthogonal flow. Direct numerical simulations have been used to verify the stability results and unravel the limits of validity of the basic flow model analyzed. The effect of the angle of attack, AoA, on the critical conditions of the non-orthogonal problem has been documented; an increase of the angle of attack, from AoA = 0 (orthogonal flow) up to values close to _/2 which make the assumptions under which the basic flow is derived questionable, is found to systematically destabilize the flow. The critical conditions of non-orthogonal flows at 0 _ AoA _ _/2 are shown to be recoverable from those of orthogonal flow, via a simple analytical transformation involving AoA. These results can help to understand the mechanisms of destabilization that occurs in the attachment line of wings at finite angles of attack. Studies taking into account variations of the pressure field in the basic flow or the extension to compressible flows are issues that remain open. El objetivo de esta tesis es estudiar los mecanismos de la inestabilidad que se producen en ciertos dispositivos aerodinámicos cuando se aumenta el ángulo de ataque. Para ello se ha utilizado un modelo simplificado del flujo de base, así como diferentes técnicas numéricas, con el fin de resolver el problema de estabilidad lineal asociado que describe el comportamiento de las perturbaciones. Estos métodos; sin y con formación de matriz, se han validado utilizando simulaciones numéricas directas con resolución espectral. De esta manera, la inestabilidad del flujo de capa límite laminar oblicuo entorno a la línea de estancamiento se aborda en un marco de análisis lineal por medio del método Bi-Global de resolución del problema de valores propios en derivadas parciales. Posteriormente se propone una extensión simple para el flujo no-ortogonal del modelo polinomial de ecuaciones diferenciales ordinarias, G¨ortler-H¨ammerlin extendido, propuesto por Theofilis et al. (2003) para el flujo ortogonal, que incluye los modelos previos como casos particulares y recupera los resultados del analisis global de estabilidad lineal. Se han realizado simulaciones directas con el fin de verificar los resultados del análisis de estabilidad así como para investigar los límites de validez del modelo de flujo base utilizado. En este trabajo se ha documentado el efecto del ángulo de ataque AoA en las condiciones críticas del problema no ortogonal obteniendo que el incremento del ángulo de ataque, de AoA = 0 (flujo ortogonal) hasta valores próximos a _/2, en el cual las hipótesis sobre las que se basa el flujo base dejan de ser válidas, tiende sistemáticamente a desestabilizar el flujo. Las condiciones críticas del caso no ortogonal 0 _ AoA _ _/2 pueden recuperarse a partir del caso ortogonal mediante el uso de una transformación analítica simple que implica el ángulo de ataque AoA. Estos resultados pueden ayudar a comprender los mecanismos de desestabilización que se producen en el borde de ataque de las alas de los aviones a ángulos de ataque finitos. Como tareas pendientes quedaría realizar estudios que tengan en cuenta variaciones del campo de presión en el flujo base así como la extensión de éste al caso de flujos compresibles.

Nonlinear description of transversal motion in a laminar boundary layer with streaks

The nonlinear streamwise growth of a spanwise periodic array of steady streaks in a flat plate boundary layer is numerically computed using the well known Reduced Navier-Stokes formulation. It is found that the flow configuration changes substantially when the amplitude of the streaks grows and the nonlinear effects come into play. The transversal motion (in the wall normal-spanwise plane), which is normally not considered, becomes non-negligible in the nonlinear regime, and it strongly distorts the streamwise velocity profiles, which end up being quite different from those predicted by the linear theory. We analyze in detail the resulting flow patterns for the nonlinearly saturated streaks, and compare them with available experimental results.

Nonlinear description of transversal motion in a laminar boundary layer with streaks

The nonlinear streamwise growth of a spanwise periodic array of steady streaks in a flat plate boundary layer is numerically computed using the well known Reduced Navier- Stokes formulation. It is found that the flow configuration changes substantially when the amplitude of the streaks grows and the nonlinear effects come into play. The transversal motion (in the wall normal-spanwise plane), which is normally not considered, becomes non-negligible in the nonlinear regime, and it strongly distorts the streamwise velocity profiles, which end up being quite different from those predicted by the linear theory. We analyze in detail the resulting flow patterns for the nonlinearly saturated streaks, and compare them with available experimental results.

Laminar-turbulent transition induced by a discrete roughness element in a supersonic boundary layer

The linear instability and breakdown to turbulence induced by an isolated roughness element in a boundary layer at Mach 2:5, over an isothermal flat plate with laminar adiabatic wall temperature, have been analysed by means of direct numerical simulations, aided by spatial BiGlobal and three-dimensional parabolized (PSE-3D) stability analyses. It is important to understand transition in this flow regime since the process can be slower than in incompressible flow and is crucial to prediction of local heat loads on next-generation flight vehicles. The results show that the roughness element, with a height of the order of the boundary layer displacement thickness, generates a highly unstable wake, which is composed of a low-velocity streak surrounded by a three-dimensional high-shear layer and is able to sustain the rapid growth of a number of instability modes. The most unstable of these modes are associated with varicose or sinuous deformations of the low-velocity streak; they are a consequence of the instability developing in the three-dimensional shear layer as a whole (the varicose mode) or in the lateral shear layers (the sinuous mode). The most unstable wake mode is of the varicose type and grows on average 17% faster tan the most unstable sinuous mode and 30 times faster than the most unstable boundary layer mode occurring in the absence of a roughness element. Due to the high growthrates registered in the presence of the roughness element, an amplification factor of N D 9 is reached within 50 roughness heights from the roughness trailing edge. The independently performed Navier–Stokes, spatial BiGlobal and PSE-3D stability results are in excellent agreement with each other, validating the use of simplified theories for roughness-induced transition involving wake instabilities. Following the linear stages of the laminar–turbulent transition process, the roll-up of the three-dimensional shear layer leads to the formation of a wedge of turbulence, which spreads laterally at a rate similar to that observed in the case of compressible turbulent spots for the same Mach number.

Accurate Parabolic Navier-Stokes solutions of the supersonic flow around and elliptic cone

Flows of relevance to new generation aerospace vehicles exist, which are weakly dependent on the streamwise direction and strongly dependent on the other two spatial directions, such as the flow around the (flattened) nose of the vehicle and the associated elliptic cone model. Exploiting these characteristics, a parabolic integration of the Navier-Stokes equations is more appropriate than solution of the full equations, resulting in the so-called Parabolic Navier-Stokes (PNS). This approach not only is the best candidate, in terms of computational efficiency and accuracy, for the computation of steady base flows with the appointed properties, but also permits performing instability analysis and laminar-turbulent transition studies a-posteriori to the base flow computation. This is to be contrasted with the alternative approach of using order-of-magnitude more expensive spatial Direct Numerical Simulations (DNS) for the description of the transition process. The PNS equations used here have been formulated for an arbitrary coordinate transformation and the spatial discretization is performed using a novel stable high-order finite-difference-based numerical scheme, ensuring the recovery of highly accurate solutions using modest computing resources. For verification purposes, the boundary layer solution around a circular cone at zero angle of attack is compared in the incompressible limit with theoretical profiles. Also, the recovered shock wave angle at supersonic conditions is compared with theoretical predictions in the same circular-base cone geometry. Finally, the entire flow field, including shock position and compressible boundary layer around a 2:1 elliptic cone is recovered at Mach numbers 3 and 4

On the Use of Matrix-Free Shift-Invert Strategies For Global Flow Instability Analysis

A novel time-stepping shift-invert algorithm for linear stability analysis of laminar flows in complex geometries is presented. This method, based on a Krylov subspace iteration, enables the solution of complex non-symmetric eigenvalue problems in a matrix-free framework. Validations and comparisons to the classical exponential method have been performed in three different cases: (i) stenotic flow, (ii) backward-facing step and (iii) lid-driven swirling flow. Results show that this new approach speeds up the required Krylov subspace iterations and has the capability of converging to specific parts of the global spectrum. It is shown that, although the exponential method remains the method of choice if leading eigenvalues are sought, the performance of the present method could be dramatically improved with the use of a preconditioner. In addition, as opposed to other methods, this strategy can be directly applied to any time-stepper, regardless of the temporal or spatial discretization of the latter.

Linear instability analysis of incompressible flow over a cuboid cavity

Direct numerical simulations are performed to analyze the three-dimensional instability of flows over three-dimensional cavities. The flow structures at different Reynolds numbers are investigated by using the spectral-element solver nek5000. As the Reynolds number increasing, the lateral wall effects become more important, the recirculation zone shrinks, the front vortex increases and the flow structure inside of the cavity becomes more complex. Results show that the flow bifurcates from a steady state to an oscillatory regime beyond a value of Reynolds number Re = 1100.