The effects of boundary-layer suction in stabilizing the laminar boundary layer were considered in this experimental work. The experiments were conducted on a flat-plate wind-tunnel model in the V.P.I. & S.U. Stability Tunnel. The capabilities of the wind tunnel in terms of mean flow uniformity and low turbulence level were established and the basic flat-plate experiment was verified by comparison with the well known stability results for the Blasius boundary-layer. The two-dimensional Tollmein-Schlichting waves were introduced into the boundary layer using a vibrating ribbon. Suction was applied through the model surface vra two porous panels which could be located at various streamwise positions on the model. The porous Dynapore surface material of these panels was adapted by Douglas Aircraft Co. for possible use as a wing surface material on aircraft equipped with Laminar Flow Control. Detailed mean-flow measurements without suction showed that the Dynapore had no destabilizing effects in the laminar boundary layer. Using the porous panels, suction could be applied either continuously or in a discrete fashion through spanwise suction strips. With suction applied through a single spanwise strip, the mean-flow effects were determined in terms of the boundary-layer shape factor. Measurements of the disturbance behavior with suction were conducted to determine the relative merits of spatially continuous suction versus suction applied through various discrete suction strip configurations. These measurements were conducted in terms of the integral across the boundary layer of the streamwise disturbance amplitude, that is A = ∫ u' I dy. These results were compared with the theory of Reed & Nayfeh (1981). A method was also proposed by this theory for optimization of suction strip placement, and measurements were made which provided partial confirmation as to the validity of this optimization scheme. Experiments were also conducted without suction to investigate the weak nonlinear two- and three-wave interactions which occur at higher wave amplitudes. In these experiments, two-frequency Tollmein Schlichting waves were introduced simultaneously using a single vibrating ribbon, and initial disturbance amplitudes were controlled. In particular, these experiments established appropriate initial conditions for comparison with analytical models and considered the role of the difference frequencies which were generated through the nonlinear interaction of the two fundamental waves. This work also considered the behavior of the harmonic waves in the nonlinear regime. / Ph. D.

Approved for public release, distribution is unlimited / A study of the performance of the Coupled Ocean Atmosphere Mesoscale Prediction System (COAMPS) was performed based on collected METOC properties affecting radar propagation during the Roughness and Evaporation Duct (RED) experiment conducted off the windward coast of Oahu, HI. The measured refractivity influencing parameters (SST, air temperature, humidity, and wind speed) were compared to COAMPS predicted values. Using the NPS bulk evaporation duct model, profiles of the modified refractivity were computed from the buoy data and compared to profiles computed from the COAMPS data. The profiles were obtained concurrently with S-Band propagation measurements along a 26-km path. The radar propagation predictions created by APM from the modified refractivity profiles, derived from the measured METOC values and COAMPS modeled values, were compared to the in situ measured propagation losses. The mean RMS error of the prop loss predictions derived from the COAMPS forecasted METOC values was <4 dB compared to a mean RMS error of <3 dB from the in situ measurement derived prop loss predictions. Significantly larger errors occurred at the COAMPS analysis times. Overall, the results are very promising for this trade wind region, where the air is cooler than the relatively warm sea surface. / Lieutenant, United States Navy

Boundary-layer flows near leading edges of generally curved obstacles have been studied for a long time. Apart from having many practical applications, the theory and approaches prevailing in this area stimulate development of a variety of computational tools and form a ground for testing them. The specific aim of this work is to study two-dimensional laminar boundary layer flows near the leading edges of airfoils and other elongated bodies, and to explore geometries for which boundary layer separation can be avoided. This class of problems is relevant to optimal design of wings, aircraft and projectile noses, laminar flow control methods and adaptive wing technology. One of the findings of this work suggests that local modifications to parabolic wing noses can yield up to 11% increase in the unseparated angle of attack. Another result obtained here is the set of shortest possible generalised elliptic noses of long symmetric bodies which allow unseparated flow. Methods adopted in this work are based on the combined use of numerically solved Prandtl equations written in Gortler variables, and inviscid solutions obtained semi-analytically by the conformal mapping method. The resulting technique being reliable, fast and computationally inexpensive, can complement or test the results obtained using a comprehensive CFD approach. / Thesis (Ph.D.)--School of Mathematical Sciences, 2002.

Laminar flow control holds major promise for increasing aircraft efficiency and increasing laminar flow over aerodynamic surfaces could decrease drag by up to 30 percent. The Flight Research Lab at Texas A&M University has studied laminar flow over a wing with 30 degrees of leading edge sweep with Discrete Roughness Elements (DREs) installed and has indicated that DREs can be used to increase laminar flow at Reynolds numbers up to 7.5 million at Mach 0.3. A new project, termed SARGE, has been commissioned in conjunction with NASA for studying DREs on a swept wing glove at conditions relevant to jet transports. The SARGE project must have an instrumentation system capable of accurately measuring flow conditions and transition location on the suction side of the glove. Infrared (IR) thermography has been selected as the primary transition detection tool. A heat transfer analysis has shown that solar radiation will warm the surface of the glove above the adiabatic wall temperature and therefore the laminar region will appear to be warmer. The FLIR SC8000 IR camera has been selected for this application due to its ability to produce high-resolution images in the appropriate IR band. High quality air data is also required for the experiment. A five-hole probe will be used to measure flow angle and velocity near the glove. This instrument will provide meanflow conditions due to its limited frequency response. High quality pressure transducers coupled with careful probe calibration will allow for differential measurements to be made with an uncertainty of +/- 0.03 degrees. Static pressure ports and high frequency response Kulite transducers will also be employed. Hotfilm sensors will be used to verify the state of the boundary layer on the glove through spectral analysis. A unique hotfilm array has been proposed that will enable the measurement of traveling wave vectors through a spectral technique. An experiment on the Flight Research Lab's Cessna O-2 to investigate the veracity of this technique has also been suggested. Thermocouples will also be installed on the glove's surface to monitor temperatures and verify transition location. The layout of the hotfilms and thermocouples is also detailed.

Thesis (M.S.)--Mississippi State University. Department of Aerospace Engineering. / Title from title screen. Includes bibliographical references.

Thesis (Ph. D.)--University of California, Riverside, 2009. / Includes abstract. Also issued in print. Includes bibliographical references. Available via ProQuest Digital Dissertations.

Not available / text

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.

Boundary-layer flows near leading edges of generally curved obstacles have been studied for a long time. Apart from having many practical applications, the theory and approaches prevailing in this area stimulate development of a variety of computational tools and form a ground for testing them. The specific aim of this work is to study two-dimensional laminar boundary layer flows near the leading edges of airfoils and other elongated bodies, and to explore geometries for which boundary layer separation can be avoided. This class of problems is relevant to optimal design of wings, aircraft and projectile noses, laminar flow control methods and adaptive wing technology. One of the findings of this work suggests that local modifications to parabolic wing noses can yield up to 11% increase in the unseparated angle of attack. Another result obtained here is the set of shortest possible generalised elliptic noses of long symmetric bodies which allow unseparated flow. Methods adopted in this work are based on the combined use of numerically solved Prandtl equations written in Gortler variables, and inviscid solutions obtained semi-analytically by the conformal mapping method. The resulting technique being reliable, fast and computationally inexpensive, can complement or test the results obtained using a comprehensive CFD approach. / Thesis (Ph.D.)--School of Mathematical Sciences, 2002.

Thesis (M. App. Sc.)--Carleton University, 2005. / Includes bibliographical references. Also available in electronic format on the Internet.