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Η εν λόγω διπλωματική εργασία αναφέρεται σε κάποια γενικά στοιχεία των μεθόδων ελέγχου του οριακού στρώματος και εστιάζεται στον έλεγχο του οριακού στρώματος με εφαρμογή της μεθόδου απορρόφησης – έγχυσης. Πιο συγκεκριμένα, στο πρώτο κεφάλαιο, με γενικό τίτλο “Οριακό Στρώμα”, αναφέρονται κάποια σύντομα ιστορικά στοιχεία και εισάγεται η έννοια του οριακού στρώματος. Στη συνέχεια, και αφού αποσαφηνιστεί η έννοια του οριακού στρώματος με τη βοήθεια εικόνων και γραφικών, εισάγονται τα χαρακτηριστικά μεγέθη αυτού. Το κεφάλαιο κλείνει με μια περιγραφή του φαινομένου της αποκόλλησης του οριακού στρώματος και των συνεπειών που η αποκόλληση αυτή επιφέρει στη ροή. Στο δεύτερο κεφάλαιο, με γενικό τίτλο “Έλεγχος του Οριακού Στρώματος”, περιγράφονται συνοπτικά οι βασικές μέθοδοι ελέγχου του οριακού στρώματος καθώς και τα πιο διαδεδομένα πεδία εφαρμογής της κάθε μιας εξ’ αυτών. Συγκεκριμένα, αναφέρονται οι μέθοδοι Κίνησης του Στερεού Ορίου (Motion of the Solid Wall), Επιτάχυνσης του Οριακού Στρώματος (Acceleration of the Boundary Layer - Blowing), Ψύξης του Τοιχώματος (Cooling of the Wall), Έγχυσης Διαφορετικού Αερίου (Injection of a Different Gas), Πρόληψης της μετάπτωσης της ροής σε τυρβώδη με κατάλληλη διαμόρφωση της γεωμετρίας του στερεού (Laminar Aerofoils) και η παράγραφος κλείνει με μια πιο εκτενή περιγραφή της μεθόδου της Απορρόφησης (Suction). Στο τρίτο κεφάλαιο, που φέρει το γενικό τίτλο “Εξισώσεις Κίνησης και Εξισώσεις Οριακού Στρώματος για Ομογενή, Ασυμπίεστα, Πραγματικά Ρευστά”, παρατίθενται οι εν λόγω εξισώσεις, ώστε να χρησιμοποιηθούν στη συνέχεια, και γίνεται μια σύντομη αναφορά στον τρόπο που, ιστορικά, αυτές παρήχθησαν. Το τέταρτο κεφάλαιο, με τίτλο “Θεωρητική Μελέτη της Μεθόδου της Απορρόφησης”, προχωράει τη μελέτη της μεθόδου απορρόφησης/έγχυσης σε επίπεδο μαθηματικών εξισώσεων. Πιο συγκεκριμένα, εισάγονται τα βασικά στοιχεία της θεωρίας και στη συνέχεια, με ένα συνδυασμό αναλυτικών και αριθμητικών διαδικασιών, πραγματοποιείται η μελέτη της απορρόφησης σε δύο συγκεκριμένα παραδείγματα. Τέλος, στο πέμπτο κεφάλαιο, με τίτλο “Εφαρμογή Απορρόφησης/Έγχυσης σε Μαγνητοϋδροδυναμική Συμπιεστή Ροή Στρωτού Οριακού Στρώματος”, μελετάται η μόνιμη, στρωτή, διδιάστατη, μαγνητοϋδροδυναμική ροή, συμπιεστού οριακού στρώματος που δημιουργείται πάνω από λεπτή, επίπεδη επιφάνεια (πλάκα), με αντίξοη βαθμίδα πίεσης και μεταφορά θερμότητας και μάζας, καθώς και τα αποτελέσματα της εφαρμογής απορρόφησης ή έγχυσης στο παραπάνω πρόβλημα. Πιο συγκεκριμένα, μετά από μια σύντομη ιστορική εισαγωγή επί του θέματος, ακολουθεί η περιγραφή του προβλήματος, καθώς και η αδιαστατοποίηση των εξισώσεων που το διέπουν. Στη συνέχεια, ακολουθεί η περιγραφή της αριθμητικής μεθόδου που χρησιμοποιείται για την επίλυση των αδιαστατοποιημένων εξισώσεων και παρατίθενται τα αποτελέσματα που προκύπτουν από τη διαδικασία αυτή της αριθμητικής επίλυσης. Το κεφάλαιο κλείνει με μια συνοπτική παράθεση των συμπερασμάτων της μελέτης του κεντρικού προβλήματος του κεφαλαίου. / This master thesis refers to some general elements of boundary layer control methods and focuses on the method of suction-injection. In particular, in Chapter I, which is simply entitled “Boundary Layer”, a short reference to some historical facts associated with this subject is being made and the general idea of boundary layer is being introduced. Following, the idea of boundary layer is being clarified with the aid of some pictures and some graphics. The chapter ends with an introduction to the phenomenon of boundary layer separation. In Chapter II, carrying the general title “Boundary Layer Control”, a short description of some of the most basic methods of boundary layer control is given and the general conditions under which each method is more effective are being briefly stated. In particular, the methods which are brought up are Motion of the Solid Wall, Acceleration of the Boundary Layer – Blowing, Cooling of the Wall, Injection of a Different Gas, Laminar Aerofoils, and the chapter ends with a more extensive description of the method of Suction. In Chapter III, entitled “Equations of Motion and Boundary Layer Equations for Homogenous, Non-Compressible, Real Fluids”, the above equations are described, with the purpose of further use in the following chapters and a short reference to the way those equations were historically introduced is being made Chapter IV, with the general title “Theoretical Study of the Method of Suction”, carries the study of the method of suction-injection to the context of mathematical equations. More specifically, basic elements of the theory are being introduced and, after that, with a combination of analytical and arithmetical techniques, two simple examples are being studied. Finally, in Chapter V entitled “Application of Suction-Injection to Magnetohydrodynamic Compressible Flow of a Laminar Boundary Layer”, the steady, laminar, two dimensional, magnetohydrodynamic flow of the compressible boundary layer which is formed over a thin flat plate, with an adverse pressure gradient and mass and heat transfer is being studied along with the results of suction-injection in the above problem. In particular, after a short historical introduction follows the description of the problem and the normalization of the equations which describe it. Then follows the description of the arithmetical method and the program being used, and the results of this procedure are stated in the next paragraph. The chapter closes with a brief description of the facts which result from the general study of the main problem of this chapter.

Thesis (Ph.D.) - Carleton University, 2007. / Includes bibliographical references (p. 251-264). Also available in electronic format on the Internet.

An experimental examination of crossflow instability and transition on a 45° swept wing is conducted in the Arizona State University Unsteady Wind Tunnel. The stationary-vortex pattern and transition location are visualized using both sublimating-chemical and liquid-crystal coatings. Extensive hot-wire measurements are conducted at several measurement stations across a single vortex track. The mean and travelling-wave disturbances are measured simultaneously. Stationary-crossflow disturbance profiles are determined by subtracting either a reference or a span-averaged velocity profile from the mean-velocity data. Mean, Stationary-crossflow, and travelling-wave velocity data are presented as local boundary-layer profiles and as contour plots across a single stationary-crossflow vortex track. Disturbance-mode profiles and growth rates are determined. The experimental data are compared to predictions from linear stability theory. Comparison of measured and predicted pressure distributions shows that a good approximation of infinite swept-wing flow is achieved. A fixed-wavelength vortex pattern is observed throughout the visualization range. The theoretically-predicted maximum-amplified vortex wavelength is found to be approximately 25% larger than the observed wavelength. Linear-stability computations for the dominant stationary-crossflow vortices show that the N-factors at transition ranged from 6.4 to 6.8. The mean-velocity profiles vary slightly across the stationary-crossflow vortex at the first measurement station. The variation across the vortex increases with downstream distance until nearly all of the profiles become highly-distorted S-shaped curves. Local stationary-crossflow disturbance profiles having either purely excess or deficit values develop at the upstream measurement stations. Further downstream the profiles take on crossover shapes not anticipated by the linear theory. The maximum streamwise stationary-crossflow velocity disturbances reach +20% of the edge velocity just before transition. The travelling-wave disturbances have single lobes at the upstream measurement stations as expected, but further downstream double-lobed travelling-wave profiles develop. The maximum disturbance intensity remains quite low until just ahead of the transition location where it suddenly peaks at 0.7% of the edge velocity and then drops sharply. The travelling-wave intensity is always more than an order of magnitude lower than the stationary crossflow-vortex strength. The mean streamwise-velocity contours are nearly flat and parallel to the model surface at the first measurement station. Further downstream, the contours rise up and begin to roll over like a wave breaking on the beach. The stationary-crossflow contours show that a plume of low-velocity fluid rises near the center of the wavelength while high-velocity regions develop near the surface at each end of the wavelength. There is no distinct pattern to the low-intensity travelling-wave contours until a short distance upstream of the transition location where the travelling-wave intensity suddenly peaks near the center of the vortex and then falls abruptly. The experimental disturbance-mode profiles agree quite well with the predicted eigenfunctions for the forward measurement stations. At the later stations, the experimental mode profiles assume double-lobed shapes with maxima above and below the single maximum predicted by the linear theory. The experimental growth rates are found to be less than or equal to the predicted growth rates from the linear theory. Also, the experimental growth rate curve oscillates over the measurement range whereas the theoretically-predicted growth rates decrease monotonically. / Ph. D.

A wing was designed with a moving surface high-lift device in the form of a rotating cylinder at the leading edge to improve low speed flight characteristics. This rotating cylinder accelerates the air flow over the top of the wing, effectively combining the concept of lift generated by an airfoil and lift generated by a rotating cylinder. This faster moving air over the top of the wing increases the pressure differential, thus increasing lift. The added momentum to the air flow results in delayed flow separation and a decrease in drag. For experimental testing, a wing was built using balsawood, basswood and MonoKote and was tested in a subsonic wind tunnel using two different tests stands. For validation and further testing, the high-lift device was modeled in Gambit and numerical simulations were performed using ANSYS Fluent. Experimental and numerical data show the high-lift device to be effective.

The boundary-layer behavior over an airplane's wings is of great importance in take-off and landing of the airplane. If its angle of attack is increased past a critical value, the flow separates from the lifting surface, resulting in a drastic loss of lift and a major increase in drag. In response to this phenomenon, many mechanisms have been studied to control the boundary-layer. First neglected because of implementation difficulties of its application, moving wall boundary-layer control methods have mainly relied on experimental research. The moving wall concept is principally applied as a rotating cylinder protruding into the airfoil. The purpose of this thesis is to provide a computational base to these experiments and to use mathematical tools of computational fluid dynamics and optimization to predict the optimum rotating speed of the cylinder, placed at the leading edge of the airfoil. For the sake of simplicity, we replace the airfoil by a flat plate with a wedge trailing edge. To model the incompressible viscous two-dimensional Navier-Stokes equations, the finite element method is applied on an unstructured two-dimensional mesh. An adaptive remeshing strategy utilized in conjunction with an error estimator controls the solution's accuracy. The aerodynamic forces acting on the total surface are computed from the finite element approximation. The ratio of the lift and the power required to move the flat plateairfoil and to rotate the cylinder forms the objective function to be optimized. A graph of the objective function versus the angle of attack is first constructed for several rotational speeds to provide a rough visual estimate of the optimum value for every angle of attack. Ultimately, an automatic optimization process provides the final solution. This results in the ideal rotational speed to be applied as the angle of attack varies. / Master of Science

Controlling systems with uncertain dynamics is crucial in systems theory, especially for unmanned vehicles operating in challenging and unknown environments. One key application involves developing control methods to ensure collision-free trajectory tracking for unmanned surface vehicles (USVs) at sea. Modern control methods for such systems often encounter unwanted high-frequency oscillations, known as chattering, in the control signals. To address this, continuous approximations of discontinuous functions in the control law have proven effective in reducing chattering. This approach is integrated into a prescribed-performance control scheme, which has previously achieved asymptotic tracking for systems with uncertain dynamics. We employ Lyapunov stability analysis to determine if theoretical bounds for error performance can be smaller than the prescribed funnel functions when incorporating continuous approximations in a boundary-layer. For both first- and second-order systems, we show that system trajectories reach an arbitrarily small boundary-layer set in finite time. This allows us to derive a priori known error bounds that are smaller than the prescribed funnels. Simulations support the theoretical results, demonstrating a significant reduction in chattering while achieving asymptotic tracking errors two orders of magnitude smaller than the funnel functions.

In this paper we consider the problem of designing dynamic compensators to control a class of nonlinear parabolic distributed parameter systems. We concentrate on a system with unbounded input and output operators governed by Burgers’ equation. This equation provide a one dimensional model for certain convection—diffusion phenomena. A linearized model is used to compute a robust controller (MinMax), a LQG controller and a fixed-order-finite-dimensional control law (Optimal Projection) by minimizing various energy functionals. These control laws are then applied to the nonlinear model. Different approximation schemes are used to design suboptimal active feedback controllers. This approach provides important practical information. In particular, we show how functional gains can be used to locate new sensors. Numerical results are given to illustrate the basic ideas and to compare the various controllers. / Ph. D.

Aerodynamic flow control using internal acoustic excitation holds promise as it combines the simplicity of passive flow control techniques (in terms of added weight and operational complexity) with the control authority of active flow control methods. While previous studies have analyzed the effects of acoustic excitation on steady wing aerodynamics, the effect of excitation on the unsteady aerodynamics is not known, which is the aim of the current effort. Internally mounted speakers on a symmetric National Advisory Committee for Aeronautics (NACA) 0012 wing are used to excite the unsteady boundary layer at the wing’s leading edge as it executes linear pitch motions ranging from quasi-steady (trailing-edge driven stall) to vortex dominated (mixed leading- and trailing-edge driven stall) motions at freestream Reynolds numbers (����) of 120, 000 and 180, 000. Experimental results show that, while acoustic excitation delays stall for quasi-steady motions, it enhances lift in the linear region and increases leading-edge vortex strength for vortex -dominated motions. The degree of change was observed to be a function of the excitation frequency. The current work establishes the effects of acoustic flow excitation in unsteady, low-���� wing aerodynamics and provides insights on the path forward to effectively implement the method for active flow control.

Simulating the exact chaotic turbulent flow field about any geometry is a dilemma between accuracy and computational resources, which has been continuously studied for just over a hundred years. This thesis is a complete walk-through of the entire process utilized to approximate the flow ingested by a Sevik-type rotor based on solutions to the Reynolds Averaged Navier-Stokes equations (RANS). The Multiple Reference Frame fluid model is utilized by the code of ANSYS-FLUENT and results are validated by experimental wake data. Three open rotor configurations are studied including a uniform inflow and the rotor near a plate with and without a thick boundary layer. Furthermore, observations are made to determine the variation in velocity profiles of the ingested turbulent flow due to varying flow conditions. / by Felipe Ferreira Lachowski. / Thesis (M.S.C.S.)--Florida Atlantic University, 2013. / Includes bibliography. / Mode of access: World Wide Web. / System requirements: Adobe Reader.