Projeto de adaptação do sistema de injeção do túnel transônico para ensaios em bocais de foguete

In this work, the project of a new experimental facility to be installed at the Aerodynamics Division of the Institute of Aeronautics and Space is presented. This new facility will provide means to perform experimental campaigns to analyze the flow behavior at different rocket nozzle concepts using cold gas that will be obtained from a modification of the Pilot Transonic Wind Tunnel air system. The new installation will enable less expensive experiments in a more secure environment, since the cold gas experimental procedures do not demand fuel storage and burn and security procedures are much less severe. Furthermore, experiments can be carried with different types of sensors, commonly used in wind tunnel tests. Also, the optical access is facilitated enabling the use of optical techniques for the characterization of flow properties inside the nozzles, such as pressure and temperature sensitive painting. The full project design and the operation conditions will be showed, as also some technical considerations about the flor behavior in the facility

Projeto de adaptação do sistema de injeção do túnel transônico para ensaios em bocais de foguete

In this work, the project of a new experimental facility to be installed at the Aerodynamics Division of the Institute of Aeronautics and Space is presented. This new facility will provide means to perform experimental campaigns to analyze the flow behavior at different rocket nozzle concepts using cold gas that will be obtained from a modification of the Pilot Transonic Wind Tunnel air system. The new installation will enable less expensive experiments in a more secure environment, since the cold gas experimental procedures do not demand fuel storage and burn and security procedures are much less severe. Furthermore, experiments can be carried with different types of sensors, commonly used in wind tunnel tests. Also, the optical access is facilitated enabling the use of optical techniques for the characterization of flow properties inside the nozzles, such as pressure and temperature sensitive painting. The full project design and the operation conditions will be showed, as also some technical considerations about the flor behavior in the facility

Measuring Aeolian Saltation: A Comparison of Sensors

SHERMAN, D.J.; LI, B.; FERRELL E.J.; ELLIS, J.T.; COX, W.D.; MAIA, L.P., and SOUSA, P.H.G.O., 2011. Measuring Aeolian Saltation: A Comparison of Sensors. In: Roberts, T.M., Rosati, J.D., and Wang, P. (eds.), Proceedings, Symposium to Honor Dr. Nicholas C. Kraus, Journal of Coastal Research, Special Issue, No. 59, pp. 280-290. West Palm Beach (Florida), ISSN 0749-0208. We report the results of field experiments designed to compare four types of aeolian saltation sensors: the Safire; the Wenglor (R) Particle Counter; the Miniphone; and the Buzzer Disc. Sets of sensors were deployed in tight spatial arrays and sampled at rates as fast as 20 kHz. In two of the three trials, the data from the sensors are compared to data obtained from sand traps. The Miniphone and the Buzzer Disc, based on microphone and piezoelectric technologies, respectively, produced grain impact counts comparable to those derived from the trap data. The Satire and the Wenglor (R) Particle Counter produce count rates that were an order of magnitude too slow. Satires undercount because of their large momentum threshold and because its signal is saturated at relatively slow transport rates. We conclude that the Miniphone and the Buzzer Disc are appropriate for deployment as grain counters because their small size allows them to be installed in closely-spaced sets.

Analisi e valutazione delle performance acustiche degli aeromobili nella fase di atterraggio

Nella tesi si analizzano le principali fonti del rumore aeronautico, lo stato dell'arte dal punto di vista normativo, tecnologico e procedurale. Si analizza lo stato dell'arte anche riguardo alla classificazione degli aeromobili, proponendo un nuovo indice prestazionale in alternativa a quello indicato dalla metodologia di certificazione (AC36-ICAO) Allo scopo di diminuire l'impatto acustico degli aeromobili in fase di atterraggio, si analizzano col programma INM i benefici di procedure CDA a 3° rispetto alle procedure tradizionali e, di seguito di procedure CDA ad angoli maggiori in termini di riduzione di lunghezza e di area delle isofoniche SEL85, SEL80 e SEL75.

Simulazione numerica di fenomeni aeroelastici con applicazione alle strutture civili

Il presente lavoro tratta lo studio dei fenomeni aeroelastici di interazione fra fluido e struttura, con il fine di provare a simularli mediante l’ausilio di un codice agli elementi finiti. Nel primo capitolo sono fornite alcune nozioni di fluidodinamica, in modo da rendere chiari i passaggi teorici fondamentali che portano alle equazioni di Navier-Stokes governanti il moto dei fluidi viscosi. Inoltre è illustrato il fenomeno della formazione di vortici a valle dei corpi tozzi dovuto alla separazione dello strato limite laminare, con descrizione anche di alcuni risultati ottenuti dalle simulazioni numeriche. Nel secondo capitolo vengono presi in rassegna i principali fenomeni di interazione fra fluido e struttura, cercando di metterne in luce le fondamenta della trattazione analitica e le ipotesi sotto le quali tale trattazione è valida. Chiaramente si tratta solo di una panoramica che non entra in merito degli sviluppi della ricerca più recente ma fornisce le basi per affrontare i vari problemi di instabilità strutturale dovuti a un particolare fenomeno di interazione con il vento. Il terzo capitolo contiene una trattazione più approfondita del fenomeno di instabilità per flutter. Tra tutti i fenomeni di instabilità aeroelastica delle strutture il flutter risulta il più temibile, soprattutto per i ponti di grande luce. Per questo si è ritenuto opportuno dedicargli un capitolo, in modo da illustrare i vari procedimenti con cui si riesce a determinare analiticamente la velocità critica di flutter di un impalcato da ponte, a partire dalle funzioni sperimentali denominate derivate di flutter. Al termine del capitolo è illustrato il procedimento con cui si ricavano sperimentalmente le derivate di flutter di un impalcato da ponte. Nel quarto capitolo è presentato l’esempio di studio dell’impalcato del ponte Tsing Ma ad Hong Kong. Sono riportati i risultati analitici dei calcoli della velocità di flutter e di divergenza torsionale dell’impalcato e i risultati delle simulazioni numeriche effettuate per stimare i coefficienti aerodinamici statici e il comportamento dinamico della struttura soggetta all’azione del vento. Considerazioni e commenti sui risultati ottenuti e sui metodi di modellazione numerica adottati completano l’elaborato.

Design and development of new pressure sensors for aerodynamic applications

This artwork reports on two different projects that were carried out during the three years of Doctor of the Philosophy course. In the first years a project regarding Capacitive Pressure Sensors Array for Aerodynamic Applications was developed in the Applied Aerodynamic research team of the Second Faculty of Engineering, University of Bologna, Forlì, Italy, and in collaboration with the ARCES laboratories of the same university. Capacitive pressure sensors were designed and fabricated, investigating theoretically and experimentally the sensor’s mechanical and electrical behaviours by means of finite elements method simulations and by means of wind tunnel tests. During the design phase, the sensor figures of merit are considered and evaluated for specific aerodynamic applications. The aim of this work is the production of low cost MEMS-alternative devices suitable for a sensor network to be implemented in air data system. The last two year was dedicated to a project regarding Wireless Pressure Sensor Network for Nautical Applications. Aim of the developed sensor network is to sense the weak pressure field acting on the sail plan of a full batten sail by means of instrumented battens, providing a real time differential pressure map over the entire sail surface. The wireless sensor network and the sensing unit were designed, fabricated and tested in the faculty laboratories. A static non-linear coupled mechanical-electrostatic simulation, has been developed to predict the pressure versus capacitance static characteristic suitable for the transduction process and to tune the geometry of the transducer to reach the required resolution, sensitivity and time response in the appropriate full scale pressure input A time dependent viscoelastic error model has been inferred and developed by means of experimental data in order to model, predict and reduce the inaccuracy bound due to the viscolelastic phenomena affecting the Mylar® polyester film used for the sensor diaphragm. The development of the two above mentioned subjects are strictly related but presently separately in this artwork.

Diagnostic techniques for EHD and MHD interaction

The impact of plasma technologies is growing both in the academic and in the industrial fields. Nowadays, a great interest is focused in plasma applications in aeronautics and astronautics domains. Plasma actuators based on the Magneto-Hydro-Dynamic (MHD) and Electro- Hydro-Dynamic (EHD) interactions are potentially able to suitably modify the fluid-dynamics characteristics around a flying body without utilizing moving parts. This could lead to the control of an aircraft with negligible response time, more reliability and improvements of the performance. In order to study the aforementioned interactions, a series of experiments and a wide number of diagnostic techniques have been utilized. The EHD interaction, realized by means of a Dielectric Barrier Discharge (DBD) actuator, and its impact on the boundary layer have been evaluated by means of two different experiments. In the first one a three phase multi-electrode flat panel actuator is used. Different external flow velocities (from 1 to 20m/s) and different values of the supplied voltage and frequency have been considered. Moreover a change of the phase sequence has been done to verify the influence of the electric field existing between successive phases. Measurements of the induced speed had shown the effect of the supply voltage and the frequency, and the phase order in the momentum transfer phenomenon. Gains in velocity, inside the boundary layer, of about 5m/s have been obtained. Spectroscopic measurements allowed to determine the rotational and the vibrational temperature of the plasma which lie in the range of 320 ÷ 440°K and of 3000 ÷ 3900°K respectively. A deviation from thermodynamic equilibrium had been found. The second EHD experiment is realized on a single electrode pair DBD actuator driven by nano-pulses superimposed to a DC or an AC bias. This new supply system separates the plasma formation mechanism from the acceleration action on the fluid, leading to an higher degree of the control of the process. Both the voltage and the frequency of the nano-pulses and the amplitude and the waveform of the bias have been varied during the experiment. Plasma jets and vortex behavior had been observed by means of fast Schlieren imaging. This allowed a deeper understanding of the EHD interaction process. A velocity increase in the boundary layer of about 2m/s had been measured. Thrust measurements have been performed by means of a scales and compared with experimental data reported in the literature. For similar voltage amplitudes thrust larger than those of the literature, had been observed. Surface charge measurements led to realize a modified DBD actuator able to obtain similar performances when compared with that of other experiments. However in this case a DC bias replacing the AC bias had been used. MHD interaction experiments had been carried out in a hypersonic wind tunnel in argon with a flow of Mach 6. Before the MHD experiments a thermal, fluid-dynamic and plasma characterization of the hypersonic argon plasma flow have been done. The electron temperature and the electron number density had been determined by means of emission spectroscopy and microwave absorption measurements. A deviation from thermodynamic equilibrium had been observed. The electron number density showed to be frozen at the stagnation region condition in the expansion through the nozzle. MHD experiments have been performed using two axial symmetric test bodies. Similar magnetic configurations were used. Permanent magnets inserted into the test body allowed to generate inside the plasma azimuthal currents around the conical shape of the body. These Faraday currents are responsible of the MHD body force which acts against the flow. The MHD interaction process has been observed by means of fast imaging, pressure and electrical measurements. Images showed bright rings due to the Faraday currents heating and exciting the plasma particles. Pressure measurements showed increases of the pressure in the regions where the MHD interaction is large. The pressure is 10 to 15% larger than when the MHD interaction process is silent. Finally by means of electrostatic probes mounted flush on the test body lateral surface Hall fields of about 500V/m had been measured. These results have been used for the validation of a numerical MHD code.

Experimental analysis of a separation control device based on plasma technology

In this thesis effects of plasma actuators based on Dielectric Barrier Discharge (DBD) technology over a NACA 0015 bidimensional airfoil have been analyzed in an experimental way, at low Reynolds number. Work developed on thesis has been carried on in partnership with the Department of Electrical Engineering of Università di Bologna, inside Wind Tunnel of the Applied Aerodynamic Laboratory of Aerospace Engineering faculty. In order to verify the effectiveness of these active control devices, the analysis has shown how actuators succeed in prevent boundary layer separation only in certain conditions af angle of attack and Reynolds numbers. Moreover, in this thesis actuators’ chordwise position effect has been also analyzed, together with the influence of steady and unsteady operations.

Dynamik orographischer Bannerwolken

Der Begriff "Bannerwolke" bezeichnet ein eindrucksvolles Phänomen aus dem Bereich der Gebirgsmeteorologie. Bannerwolken können gelegentlich im Hochgebirge im Bereich steiler Bergspitzen oder langgezogener Bergrücken, wie z.B. dem Matterhorn in den Schweizer Alpen oder dem Zugspitzgrat in den Bayrischen Alpen beobachtet werden. Der Begriff bezeichnet eine Banner- oder Fahnen-ähnliche Wolkenstruktur, welche an der windabgewandten Seite des Berges befestigt zu sein scheint, während die windzugewandte Seite vollkommen wolkenfrei ist. Bannerwolken fanden bislang, trotz ihres relativ häufigen Auftretens in der wissenschaftlichen Literatur kaum Beachtung. Entsprechend wenig ist über ihren Entstehungsmechanismus und insbesondere die relative Bedeutung dynamischer gegenüber thermodynamischer Prozesse bekannt. In der wissenschaftlichen Literatur wurden bislang 3 unterschiedliche Mechanismen postuliert, um die Entstehung von Bannerwolken zu erklären. Demnach entstehen Bannerwolken durch (a) den Bernoulli-Effekt, insbesondere durch die lokale adiabatische Kühlung hervorgerufen durch eine Druckabnahme entlang quasi-horizontal verlaufender, auf der windzugewandten Seite startender Trajektorien, (b) durch isobare Mischung bodennaher kälterer Luft mit wärmerer Luft aus höheren Schichten, oder (c) durch erzwungene Hebung im aufsteigenden Ast eines Leerotors. Ziel dieser Arbeit ist es, ein besseres physikalisches Verständnis für das Phänomen der Bannerwolke zu entwickeln. Das Hauptaugenmerk liegt auf dem dominierenden Entstehungsmechanismus, der relativen Bedeutung dynamischer und thermodynamischer Prozesse, sowie der Frage nach geeigneten meteorologischen Bedingungen. Zu diesem Zweck wurde ein neues Grobstruktursimulations (LES)-Modell entwickelt, welches geeignet ist turbulente, feuchte Strömungen in komplexem Terrain zu untersuchen. Das Modell baut auf einem bereits existierenden mesoskaligen (RANS) Modell auf. Im Rahmen dieser Arbeit wurde das neue Modell ausführlich gegen numerische Referenzlösungen und Windkanal-Daten verglichen. Die wesentlichen Ergebnisse werden diskutiert, um die Anwendbarkeit des Modells auf die vorliegende wissenschaftliche Fragestellung zu überprüfen und zu verdeutlichen. Die Strömung über eine idealisierte pyramidenförmige Bergspitze wurde für Froude-Zahlen Fr >> 1 sowohl auf Labor- als auch atmosphärischer Skala mit und ohne Berücksichtigung der Feuchtephysik untersucht. Die Simulationen zeigen, dass Bannerwolken ein primär dynamisches Phänomen darstellen. Sie entstehen im Lee steiler Bergspitzen durch dynamisch erzwungene Hebung. Die Simulationen bestätigen somit die Leerotor-Theorie. Aufgrund des stark asymmetrischen, Hindernis-induzierten Strömungsfeldes können Bannerwolken sogar im Falle horizontal homogener Anfangsbedingungen hinsichtlich Feuchte und Temperatur entstehen. Dies führte zu der neuen Erkenntnis, dass zusätzliche leeseitige Feuchtequellen, unterschiedliche Luftmassen in Luv und Lee, oder Strahlungseffekte keine notwendige Voraussetzung für die Entstehung einer Bannerwolke darstellen. Die Wahrscheinlichkeit der Bannerwolkenbildung steigt mit zunehmender Höhe und Steilheit des pyramidenförmigen Hindernisses und ist in erster Näherung unabhängig von dessen Orientierung zur Anströmung. Simulationen mit und ohne Berücksichtigung der Feuchtephysik machen deutlich, dass thermodynamische Prozesse (insbes. die Umsetzung latenter Wärme) für die Dynamik prototypischer (nicht-konvektiver) Bannerwolken zweitrangig ist. Die Verstärkung des aufsteigenden Astes im Lee und die resultierende Wolkenbildung, hervorgerufen durch die Freisetzung latenter Wärme, sind nahezu vernachlässigbar. Die Feuchtephysik induziert jedoch eine Dipol-ähnliche Struktur im Vertikalprofil der Brunt-Väisälä Frequenz, was zu einem moderaten Anstieg der leeseitigen Turbulenz führt. Es wird gezeigt, dass Gebirgswellen kein entscheidendes Ingredienz darstellen, um die Dynamik von Bannerwolken zu verstehen. Durch eine Verstärkung der Absinkbewegung im Lee, haben Gebirgswellen lediglich die Tendenz die horizontale Ausdehnung von Bannerwolken zu reduzieren. Bezüglich geeigneter meteorologischer Bedingungen zeigen die Simulationen, dass unter horizontal homogenen Anfangsbedingungen die äquivalentpotentielle Temperatur in der Anströmung mit der Höhe abnehmen muss. Es werden 3 notwendige und hinreichende Kriterien, basierend auf dynamischen und thermodynamischen Variablen vorgestellt, welche einen weiteren Einblick in geeignete meteorologische Bedingungen geben.

Aereodynamics of dry helically-filleted bridge cables

Dry limited amplitude vibrations flow-transition induced vibrations were experienced on a helically-filleted tube, in a previous study performed by Kleissl and Georgakis (2012). These vibrations have never been reported in previous studies. A deep study on the same inclined-yawed cable configuration has been performed, in order to investigate and further understand the nature of these vibrations. The investigation has been carried out through passive-dynamic wind tunnel tests in the Climatic Wind Tunnel at FORCE Technology, Kgs. Lyngby, Denmark. The results are carried out in terms of aerodynamic damping and peak to peak amplitude at different flow velocities and different boundary conditions. The latter are done by testing the model with and without the spray system installed in the wind tunnel cross section, in order to understand and evaluate the influence of the spray system on the start of the vibrations mechanism and on the flow turbulence. The gained experiences are finally presented for the use in future testing activities with the purpose of improving the performance of passive-dynamic tests.

Aeroelastic stability of structures: flutter analysis using Computational Fluid Dynamics

Thanks to the increasing slenderness and lightness allowed by new construction techniques and materials, the effects of wind on structures became in the last decades a research field of great importance in Civil Engineering. Thanks to the advances in computers power, the numerical simulation of wind tunnel tests has became a valid complementary activity and an attractive alternative for the future. Due to its flexibility, during the last years, the computational approach gained importance with respect to the traditional experimental investigation. However, still today, the computational approach to fluid-structure interaction problems is not as widely adopted as it could be expected. The main reason for this lies in the difficulties encountered in the numerical simulation of the turbulent, unsteady flow conditions generally encountered around bluff bodies. This thesis aims at providing a guide to the numerical simulation of bridge deck aerodynamic and aeroelastic behaviour describing in detail the simulation strategies and setting guidelines useful for the interpretation of the results.

Contributo sperimentale alla ridefinizione della diffusione in parete della camera di prova della galleria del vento Dallara

Joseph Nicolas Cugnot built the first primitive car in 1769 and approximately one hundred year later the first automotive race took place. Thanks to this, for the first time the aerodynamics principles began to be applied to cars. The aerodynamic study of a car is important to improve the performance on the road, or on the track. It purposely enhances the stability in the turns and increases the maximum velocity. However, it is also useful, decrease the fuel consumption, in order to reduce the pollution. Given that cars are a very complex body, the aerodynamic study cannot be conducted following an analytical method, but it is possible, in general, to choose between two different approaches: the numerical or the experimental one. The results of numerical studies depend on the computers’ potential and on the method use to implement the mathematical model. Today, the best way to perform an aerodynamic study is still experimental, which means that in the first phase of the design process the study is performed in a wind tunnel and in later phases directly on track. The automotive wind tunnels are singular mainly due to the test chamber, which typically contains a ground simulation system. The test chamber can have different types of walls: open walls, closed walls, adaptive walls or slotted walls. The best solution is to use the slotted walls because they minimize the interference between the walls and the streamlines, the interaction between the flow and the environment, and also to contain the overall costs. Furthermore, is necessary minimize the boundary layer at the walls, without accelerating the flow, in order to provide the maximum section of homogeneous flow. This thesis aims at redefining the divergent angle of the Dallara Automobili S.P.A. wind tunnel’s walls, in order to improve the overall homogeneity. To perform this study it was necessary to acquire the pressure data of the boundary layer, than it was created the profile of the boundary layer velocity and, to minimize the experimental errors, it was calculated the displacement thickness. The results obtained shows, even if the instrument used to the experiment was not the best one, that the boundary layer thickness could be minor in case of a low diffusion angle. So it is convenient to perform another experiment with a most sensitive instrument to verified what is the better wall configuration.

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.