Analisi della qualità del flusso di una galleria del vento per uso didattico

La galleria del vento "Wintaer" (WINd Tunnel itAER) è una piccola galleria subsonica con flusso incomprimibile utilizzata per scopi didattici, dotata di ventola assiale "Varofoil" a passo variabile per la regolazione della velocità del flusso. Lo scopo di questo elaborato è analizzare la qualità del flusso della galleria al fine di determinare le prestazioni del sistema ed alcune proprietà fondamentali, ovvero l'uniformità spaziale del flusso attraverso l'acquisizione di profili di velocità e l'intensità di turbolenza. Dalla conduzione delle prove sperimentali è emerso che la galleria permette il raggiungimento di un range di velocità compreso tra i 16 m/s e i 43 m/s, ha poca uniformità spaziale e presenta alti livelli di turbolenza. Per quanto riguarda il range di velocità si sono riscontrate problematiche relative all'impossibilità di raggiungere le basse velocità (fino a 7 m/s) a causa, molto probabilmente, di blocchi meccanici che limitano l'intervallo di angoli di calettamento (e quindi il passo) delle pale della ventola, ed è quindi necessario l'intervento della ditta per effettuare un'operazione di revisione della ventola. Relativamente ai profili di velocità, acquisiti con tubo di Pitot, e all'intensità di turbolenza, acquisita con anemometro a filo caldo, è emerso che i risultati sono stati disturbati da errori introdotti a causa dell'instabilità termica della galleria, ovvero un aumento progressivo di temperatura nell'impianto. Tale instabilità può essere risolta rimettendo in funzione l'unità di scambio di calore di cui la galleria è equipaggiata. L'attendibilità dei risultati ottenuti è quindi condizionata dall'instabilità termica, dunque, per una più preciso studio della qualità del flusso è necessario effettuare le prove sperimentali in condizioni di stabilità termica, la quale sarà essa stessa oggetto di analisi una volta rimesso in funzione il sistema di raffreddamento. Infine sono proposte soluzioni per il miglioramento della geometria dell'impianto, poco efficiente, in particolare per quanto riguarda i raddrizzatori di filetti fluidi (honeycombs) e il raccordo tra convergente e camera di prova, per il passaggio dalla sezione circolare del convergente a quella rettangolare della camera di prova. Si suggerisce lo spostamento di tale raccordo a monte della camera di calma, l'adozione di un convergente a sezione rettangolare e di una camera di calma a sezione rettangolare con honeycombs esagonali e l'aggiunta di reti per la diminuzione della turbolenza del flusso.

Windkanalstudien zum Graupelwachstum und Bestimmung von Retentionskoeffizienten verschiedener Spurengase während der Bereifung

Am vertikalen Windkanal der Johannes Gutenberg-Universität Mainz wurden physikalische und chemische Bereifungsexperimente durchgeführt. Dabei lagen die Umgebungstemperaturen bei allen Experimenten zwischen etwa -15 und -5°C und der Flüssigwassergehalt erstreckte sich von 0,9 bis etwa 1,6g/m³, typische Bedingungen für Mischphasenwolken in denen Bereifung stattfindet. Oberflächentemperaturmessungen an wachsenden hängenden Graupelpartikeln zeigten, dass während der Experimente trockene Wachstumsbedingungen herrschten.rnZunächst wurde das Graupelwachstum an in einer laminaren Strömung frei schwebenden Eispartikeln mit Anfangsradien zwischen 290 und 380µm, die mit flüssigen unterkühlten Wolkentröpfchen bereift wurden, studiert. Ziel war es, den Kollektionskern aus der Massenzunahme des bereiften Eispartikels und dem mittleren Flüssigwassergehalt während des Wachstumsexperimentes zu bestimmen. Die ermittelten Werte für die Kollektionskerne der bereiften Eispartikel erstreckten sich von 0,9 bis 2,3cm³/s in Abhängigkeit ihres Kollektorimpulses (Masse * Fallgeschwindigkeit des bereifenden Graupels), der zwischen 0,04 und 0,10gcm/s lag. Bei den Experimenten zeigte sich, dass die hier gemessenen Kollektionskerne höher waren im Vergleich mit Kollektionskernen flüssiger Tropfen untereinander. Aus den aktuellen Ergebnissen dieser Arbeit und der vorhandenen Literaturwerte wurde ein empirischer Faktor entwickelt, der von dem Wolkentröpfchenradius abhängig ist und diesen Unterschied beschreibt. Für die untersuchten Größenbereiche von Kollektorpartikel und flüssigen Tröpfchen können die korrigierten Kollektionskernwerte in Wolkenmodelle für die entsprechenden Größen eingebunden werden.rnBei den chemischen Experimenten zu dieser Arbeit wurde die Spurenstoffaufnahme verschiedener atmosphärischer Spurengase (HNO3, HCl, H2O2, NH3 und SO2) während der Bereifung untersucht. Diese Experimente mussten aus technischen Gründen mit hängenden Eispartikeln, dendritischen Eiskristallen und Schneeflocken, bereift mit flüssigen Wolkenlösungströpfchen, durchgeführt werden.rnDie Konzentrationen der Lösung, aus der die Wolkentröpfchen mit Hilfe von Zweistoffdüsen erzeugt wurden, lagen zwischen 1 und 120mg/l. Für die Experimente mit Ammoniak und Schwefeldioxid wurden Konzentrationen zwischen 1 und 22mg/l verwendet. Das Schmelzwasser der bereiften hängenden Graupel und Schneeflocken wurden ionenchromatographisch analysiert und zusammen mit der bekannten Konzentration der bereifenden Wolkentröpfchen konnte der Retentionskoeffizient für jeden Spurenstoff bestimmt werden. Er gibt die Menge an Spurenstoff an, die bei der Phasenumwandlung von flüssig zu fest in die Eisphase übergeht. Salpetersäure und Salzsäure waren nahezu vollständig retiniert (Mittelwerte der gesamten Experimente entsprechend 99±8% und 100±9%). Für Wasserstoffperoxid wurde ein mittlerer Retentionskoeffizient von 65±17% bestimmt. rnDer mittlere Retentionskoeffizient von Ammoniak ergab sich unabhängig vom Flüssigwassergehalt zu 92±21%, während sich für Schwefeldioxid 53±10% für niedrige und 29±7% für hohe Flüssigphasenkonzentrationen ergaben. Bei einigen der untersuchten Spurenstoffe wurde eine Temperaturabhängigkeit beobachtet und wenn möglich durch Parametrisierungen beschrieben.rn

Formulazione e messa a punto di una metodologia per il progetto di ventilatori per gallerie del vento con applicazione al "long-pipe" del laboratorio CICLoPE : analisi attraverso l'impiego di modelli matematici in MATLAB

Nell'ottica di un futuro riprogetto, totale o parziale, del ventilatore della galleria del vento del progetto CICLoPE dell'Università di Bologna, è stato messo a punto, grazie a modelli matematici di letteratura, un algoritmo per la determinazione della geometria delle pale di un fan. La procedura si basa su ipotesi di incompressibilità e assenza di vortici di estremità ed è in grado di fornire la geometria del ventilatore una volta che sono state fissate: le condizioni richieste nella sezione di test, l'efficienza del tunnel e alcune proprietà del ventilatore stesso (ad esempio tipologia di profilo aerodinamico e numero di pale). L'algoritmo è in grado di lavorare solamente con la configurazione ventilatore seguito da profili raddrizzatori, ma è in previsione un'estensione che consentirà di studiare anche la configurazione a fan controrotanti (come quella del CICLoPE). Con questo software sono state progettate numerose soluzioni diverse per studiare il legame tra rendimento e geometria del ventilatore. Inoltre sono stati individuati i parametri che permettono di ottenere una pala con rastremazione e svergolatura trascurabili, con lo scopo di abbassare i costi del manufatto. In particolare è stato dimostrato come le configurazioni con diametro della nacelle grande (superiore al 65\% del diametro della sezione di potenza) siano particolarmente adatte a fornire rendimenti alti con la minima complicatezza della pala. Per quanto riguarda l'efficienza aerodinamica del profilo, i test comparativi indicano che questo parametro influisce relativamente poco sul rendimento del macchinario ma modifica profondamente la geometria della pala. Efficienze elevate tendono, secondo lo studio, a richiedere pale estremamente rastremate e poco svergolate; questo porta a preferire l'adozione di profili mediamente efficienti ma dall'ampio intervallo operativo in termini di angolo di attacco.

Energy harvesting from piezoelectric devices embedded in a 3D printed wing

This thesis work has been carried out at Clarkson University in Potsdam NY, USA and involved the design of a low elongation wing, consisting of parts made by polylactide (PLA) using the fused deposition model (FDM) technology of Rapid Prototyping, then assembled together in a thin aluminum spar. The aim of the research is to evaluate the feasibility of collecting electrical energy by converting mechanical energy from the vibration of the wing flutter. With this aim piezoelectric stripes were glued in the inner part of the wing, as well as on the aluminum spar, as monomorphic configuration. During the phases of the project, particular attention was given to the geometry and the materials used, in order to trigger the flutter for low flow velocity. The CAD software SolidWorks® was used for the design of the wing and then the drawings were sent to the Clarkson machine shop in order to to produce the parts required by the wing assembly. FEM simulations were performed, using software MSC NASTRAN/PATRAN®, to evaluate the stiffness of the whole wing as well as the natural vibration modes of the structure. These data, in a first approximation, were used to predict the flutter speed. Finally, experimental tests in the Clarkson wind tunnel facility were carried out in order to validate the results obtained from FEM analysis. The power collected by the piezoelectrics under flutter condition was addressed by tuning the resistors downstream the electronic circuit of the piezoelectrics.

Studies of spatial clustering of inertial particles in turbulence

We present studies of the spatial clustering of inertial particles embedded in turbulent flow. A major part of the thesis is experimental, involving the technique of Phase Doppler Interferometry (PDI). The thesis also includes significant amount of simulation studies and some theoretical considerations. We describe the details of PDI and explain why it is suitable for study of particle clustering in turbulent flow with a strong mean velocity. We introduce the concept of the radial distribution function (RDF) as our chosen way of quantifying inertial particle clustering and present some original works on foundational and practical considerations related to it. These include methods of treating finite sampling size, interpretation of the magnitude of RDF and the possibility of isolating RDF signature of inertial clustering from that of large scale mixing. In experimental work, we used the PDI to observe clustering of water droplets in a turbulent wind tunnel. From that we present, in the form of a published paper, evidence of dynamical similarity (Stokes number similarity) of inertial particle clustering together with other results in qualitative agreement with available theoretical prediction and simulation results. We next show detailed quantitative comparisons of results from our experiments, direct-numerical-simulation (DNS) and theory. Very promising agreement was found for like-sized particles (mono-disperse). Theory is found to be incorrect regarding clustering of different-sized particles and we propose a empirical correction based on the DNS and experimental results. Besides this, we also discovered a few interesting characteristics of inertial clustering. Firstly, through observations, we found an intriguing possibility for modeling the RDF arising from inertial clustering that has only one (sensitive) parameter. We also found that clustering becomes saturated at high Reynolds number.

Rapid Tooling via Stereolithography

Approximately three years ago, composite stereolithography (SL) resins were introduced to the marketplace, offering performance features beyond what traditional SL resins could offer. In particular, the high heat deflection temperatures and high stiffness of these highly filled resins have opened the door to several new rapid prototyping (RP) applications, including wind tunnel test modelling and, more recently, rapid tooling.

Tab 1-4 Weight and volume reduction as well as surface subsidence during abrasion experiments

Antarctic land surfaces in South Victoria Land, all without a covering of vegetation, are actively formed by winds which often reach velocities of more than 100 km/h. Consequently, deflation and abrasion are essential factors in the process of slope formation. Water erosion, active only during the very short summer period, is limited to a few localities in South Victoria Land. Experiments in a wind tunnel proved that ventifacts in the Dry Valleys can be formed within a few decades or at the most, a few centuries. Yearly corrasion rates average around a maximum of a few millimeters. Considerable variability is caused by the different exposures of ventifacts within the micro relief end the varying resistance of the rocks. The importance of ice crystals (snow) for abrasion processes should not be overestimated.

The ballast pick-up problem. A theoretical approach and two experimental campaigns

The aim of this contribution is to present a theoretical approach and two experimental campaigns (on wind tunnel and on the track) concerning the research work about the ballast train-induced-wind erosion (BTIWE) phenomenon. When a high speed train overpasses the critical speed, it produces a wind speed close to the track large enough to start the motion of the ballast elements, eventually leading to the rolling of the stones (Kwon and Park, 2006) and, if these stones get enough energy, they can jump and then initiate a saltation-like chain reaction, as found in the saltation processes of soil eolian erosion (Bagnold, 1941). The expelled stones can reach a height which is larger than the lowest parts of the train, striking them (and the track surroundings) producing considerable damage that should be avoided. There is not much published work about this phenomenon, in spite of the great interest that exists due to its relevant applications in increasing the maximum operative train speed. Particularly, the initiation of flight of ballast due to the pass of a high speed train has been studied by Kwon and Park (2006) by performing field and wind tunnel experiments.

Aerodynamic Analysis of Open Trailing Edge Airfoils at Low Reynolds Number

A study has been made on the influence of the open trailing edge in airfoils used in different devices relating their aerodynamic performances. Wind tunnel tests have been made at different Reynolds numbers and angles of attack in order to show this effect. Besides, a quantitative study of the aerodynamic properties has been made based on the different trailing edge thickness

Numerical and Experimental Studies of Sail Aerodynamics

The purpose of this investigation was the determination of the aerodynamic performance of sails and gain knowledge of the phenomena involved in order to improve the aerody¬namic characteristics. In this research, the airflow around different sails in four scenarios was studied. The method to analyze these scenarios was the combination of numerical simulations and experimental tests by taking advantage of the best of each tool. Two different Com¬putational Fluid Dynamic codes were utilized: the ANSYS-CFX and the CD-Adapco’s STAR-CCM+. The experimental tests were conducted in the Atmospheric Boundary Layer Wind Tunnel at the Universidad de Granada (Spain), the Twisted Flow Wind Tunnel at the University of Auckland (New Zealand) and the A9 Wind Tunnel at the Universidad Polit´ecnica de Madrid (Spain). Through this research, it was found the three-dimensional effect of the mast on the aerodynamic performance of an IMS Class boat. The pressure distribution on a Transpac 52 Class mainsail was also determined. Moreover, the aerodynamic perfor¬mance of the 43ft and 60ft Dhow Classes was obtained. Finally, a feasibility study was conducted to use a structural wing in combination with conventional propulsions systems. The main conclusion was that this research clarified gaps on the knowledge of the aerodynamic performance of sails. Moreover, since commercial codes were not specifically designed to study sails, a procedure was developed. On the other hand, innovative experimental techniques were used and applied to model-scale sails. The achievements of this thesis are promising and some of the results are already in use by the industry on a daily basis. El propósito de este estudio era determinar el comportamiento aerodinámico de unas velas y mejorar el conocimiento de los fenómenos que suceden para optimizar las características aerodinámicas de dichas velas. En esta investigación se estudió el flujo de aire alrededor de diferentes velas en cuatro escenarios. El método para analizar estos escenarios fue la combinación de simulaciones numéricas y ensayos experimentales mediante el aprovechamiento de las ventajas de cada herramienta. Se utilizaron dos códigos de dinámica de fluidos computacional: el ANSYS-CFX y el STAR-CCM+ de la empresa CD-Adapco. Los ensayos experimentales se desarrollaron en el túnel de viento de capa límite de la Universidad de Granada (España), el túnel de viento de la Universidad de Auckland (Nueva Zelanda) y en el túnel A9 de la Universidad Politécnica de Madrid (España). Mediante esta investigación, se determinó el efecto tridimensional del mástil en un velero de la clase IMS. También se describió la distribución de presiones sobre una mayor de un Transpac 52. Además, se obtuvo el comportamiento aerodinámico de las clases 43ft y 60ft de los veleros Dhows. Finalmente, se llevó a cabo un estudio de viabilidad de la utilización de un ala estructural en combinación con sistemas de propulsión convencionales. La conclusión principal de esta investigación fue la capacidad de explicar ciertas lagunas en el conocimiento del comportamiento aerodinámico de las velas en diferentes escenarios. Además, dado que los códigos comerciales no están específicamente diseñados para el estudio de velas, se desarrolló un procedimiento a tal efecto. Por otro lado, se han utilizado innovadoras técnicas experimentales y se han aplicado a modelos de velas a escala. Los logros de esta investigación son prometedores y algunos de los resultados obtenidos ya están siendo utilizados por la industria en su día a día.

Lift devices in the flight of Archaeopteryx

Archaeopteryx has played a central role in the debates on the origins of avian (and dinosaurian) flight, even though as a flier it probably represents a relatively late stage in the beginnings of fl ight. We report on aerodynamic tests using a life-sized model of Archaeopteryx performing in a low turbulence wind tunnel. Our results indicate that tail deflection significantly decreased take-off velocity and power consumption, and that the first manual digit could have functioned as the structural precursor of the alula. Such results demonstrate that Archaeopteryx had already evolved high-lift devices, which are functional analogues of those present in today's birds.

Hysteresis phenomena in transverse galloping of triangular cross-section bodies

Transverse galloping is a type of aeroelastic instability characterised by large amplitude, low frequency oscillation of a structure in the direction normal to the mean wind direction. It normally appears in bodies with small stiffness and structural damping, provided the incident flow velocity is high enough. In the simplest approach transverse galloping can be considered as a one-degree-of-freedom oscillator subjected to aerodynamic forces, which in turn can be described by using a quasi-steady description. In this frame it has been demonstrated that hysteresis phenomena in transverse galloping is related to the existence of inflection points in the curve giving the dependence with the angle of attack of the aerodynamic coefficient normal to the incident flow. Aiming at experimentally checking such a relationship between these inflection points and hysteresis, wind tunnel experiments have been conducted. Experiments have been restricted to isosceles triangular cross-section bodies, whose galloping behaviour is well documented. Experimental results show that, according to theoretical predictions, hysteresis takes place at the angles of attack where there are inflection points in the lift coefficient curve, provided that the body is prone to gallop at these angles of attack.

Influence of open trailing edge on laminar aerofoils at low Reynols number

This article deals with the effect of open trailing edge on the aerodynamic characteristics of laminar aerofoils at low Reynolds numbers, the attention being focussed on the influence of such a trailingedge imperfection on the aerodynamic efficiency. Wind tunnel tests have been performed at different Reynolds numbers and angles of attack, and global aerodynamic as well as pressure distributions were measured (in these tests two types of open trailing edges, either sharp or rounded were considered). From experimental results, a quantitative analysis of the influence of the trailing-edge thickness on the degradation of aerofoil aerodynamic performances has been obtained, which allows the establishment of a criterion for an acceptance limit for this kind of imperfection.

Experimental investigation on box-wing configuration for UAS

The range for airframe configurations available for UAS is as diverse as those used for manned aircraft and more since the commercial risk in trying unorthodox solutions is less for the UAS manufacturer. This is principally because the UAS airframes are usually much smaller than the manned aircraft and operators are less likely to have a bias against unconventional configurations. One of these unconventional configurations is the box-wing, which is an unconventional solution for the design of the new UAS generation. The existence of two wings separated in different planes that are, however, significantly close together, means that the aerodynamic analysis by theoretical or computational methods is a difficult task, due to the considerable interference existing. Considering the fact that the flight of most UAS takes place at low Reynolds numbers, it is necessary to study the aerodynamics of the box wing configuration by testing different models in a wind tunnel to be able to obtain reasonable results. In the present work, the study is enhanced by varying not only the sweepback angles of the two wings, but also their position along the models’ fuselage. Certain models have shown being more efficient than others, pointing out that certain relative positions of wing exists that can improve the aerodynamics efficiency of the box wing configuration.

Effect of the Wake of the Transducer Supports on the Ultrasonic Anemometer Measurements

The wake produced by the structural supports of the ultrasonic anemometers (UAs)causes distortions in the velocity field in the vicinity of the sonic path. These distortions are measured by the UA, inducing errors in the determination of the mean velocity, turbulence intensity, spectrum, etc.; basic parameters to determine the effect of wind on structures. Additionally, these distortions can lead to indefinition in the calibration function of the sensors (Cuerva et al., 2004). Several wind tunnel tests have been dedicated to obtaining experimental data, from which have been developed fit models to describe and to correct these distortions (Kaimal, 1978 and Wyngaard, 1985). This work explores the effect of a vortex wake generated by the supports of an UA, on the measurement of wind speed done by this instrument. To do this, the Von Karman¿s vortex street potential model is combined with the mathematical model of the measuring process carried out by UAs developed by Franchini et al. (2007). The obtained results are the correction functions of the measured wind velocity, which depends on the geometry of the sonic anemometer and aerodynamic conditions. These results have been validated with the ones obtained in a wind tunnel test done on a single path UA, especially developed for research. The supports of this UA have been modified in order to reproduce the conditions of the theoretical model. Good agreements between experimental and theoretical results have been found.