subject:(swept)

University of Miami

1. Bennett, Christopher Lee. Acquisition of Otoacoustic Emissions Using Swept-Tone Techniques.

Degree: PhD, Biomedical Engineering (Engineering), 2010, University of Miami

URL: https://scholarlyrepository.miami.edu/oa_dissertations/454

► Otoacoustic emissions (OAEs) have been under investigation since their discovery 30 years ago (Kemp, 1978). Otoacoustic emissions are quiet sounds generated within the cochlea… (more)

▼ Otoacoustic emissions (OAEs) have been under investigation since their discovery 30 years ago (Kemp, 1978). Otoacoustic emissions are quiet sounds generated within the cochlea that can be detected with a sensitive microphone placed within the ear canal. They are used clinically as a hearing screening tool but have the potential for diagnostic and monitoring purposes. For this dissertation, high-resolution instrumentation was developed for improving the acquisition of OAEs. It was shown that a high bit-depth device is required in order to simultaneously characterize the ear canal and the cochlear responses. This led to a reduction in the stimulus artifact that revealed early latency, high-frequency otoacoustic emissions. Next, a swept-tone technique originally developed for use in acoustical systems was formally developed for use in the human ear. The swept-tone technique allows for the simultaneous acquisition of a system's impulse response and its distortion components. The swept-tone was first used in this study to characterize the ear canal transfer properties. From that transfer function, a compensation routine was developed which equalized the magnitude and phase distortions of the ear canal. As a result, an improved acoustical click could be presented to the ear, which allowed for further reduction of the stimulus artifact, revealing early latency emissions. Spectral flatness and effective duration measurements of the compensated click showed an improvement over traditional click stimuli. Furthermore, wavelet analysis and time-frequency latency computations showed that higher frequency otoacoustic emissions were recoverable when using a compensated click stimulus. The swept-tone technique was then utilized for the direct acquisition of otoacoustic emissions. The swept-tone response was compressed to an impulse response and compared to a standard click response. It was found that several similarities exist between the two response types. The divergences, primarily in the low-frequencies, have implications in the generation mechanisms involved in a click-evoked otoacoustic emission. The swept-tone response provided some clinical benefits, namely in an improved signal-to-noise ratio, and in the removal of obstructive synchronized spontaneous OAEs when compared to a standard click response. Current methods are restricted by noise contamination, and the use of a swept-tone technique can reduce the acquisition time by up to a factor of four, compared to standard click methods. These implications and future potential studies are discussed. Advisors/Committee Members: Ozcan Ozdamar, Jorge Bohorquez, Fred Telischi, Rafael Delgado, Colby Leider.

Subjects/Keywords: Swept-sine Analysis; TEOAE; Time-frequency; Audiometry

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APA (6^th Edition):

Bennett, C. L. (2010). Acquisition of Otoacoustic Emissions Using Swept-Tone Techniques. (Doctoral Dissertation). University of Miami. Retrieved from https://scholarlyrepository.miami.edu/oa_dissertations/454

Chicago Manual of Style (16^th Edition):

Bennett, Christopher Lee. “Acquisition of Otoacoustic Emissions Using Swept-Tone Techniques.” 2010. Doctoral Dissertation, University of Miami. Accessed January 25, 2021. https://scholarlyrepository.miami.edu/oa_dissertations/454.

MLA Handbook (7^th Edition):

Bennett, Christopher Lee. “Acquisition of Otoacoustic Emissions Using Swept-Tone Techniques.” 2010. Web. 25 Jan 2021.

Vancouver:

Bennett CL. Acquisition of Otoacoustic Emissions Using Swept-Tone Techniques. [Internet] [Doctoral dissertation]. University of Miami; 2010. [cited 2021 Jan 25]. Available from: https://scholarlyrepository.miami.edu/oa_dissertations/454.

Council of Science Editors:

Bennett CL. Acquisition of Otoacoustic Emissions Using Swept-Tone Techniques. [Doctoral Dissertation]. University of Miami; 2010. Available from: https://scholarlyrepository.miami.edu/oa_dissertations/454

Johannes Gutenberg Universität Mainz

2. Dziegielewski, Andreas von. High precision swept volume approximation with conservative error bounds.

Degree: 2012, Johannes Gutenberg Universität Mainz

URL: http://ubm.opus.hbz-nrw.de/volltexte/2012/3267/

►

In technical design processes in the automotive industry, digital prototypes rapidly gain importance, because they allow for a detection of design errors in early development… (more)

▼

In technical design processes in the automotive industry, digital prototypes rapidly gain importance, because they allow for a detection of design errors in early development stages. The technical design process includes the computation of swept volumes for maintainability analysis and clearance checks. The swept volume is very useful, for example, to identify problem areas where a safety distance might not be kept. With the explicit construction of the swept volume an engineer gets evidence on how the shape of components that come too close have to be modified.rnIn this thesis a concept for the approximation of the outer boundary of a swept volume is developed. For safety reasons, it is essential that the approximation is conservative, i.e., that the swept volume is completely enclosed by the approximation. On the other hand, one wishes to approximate the swept volume as precisely as possible. In this work, we will show, that the one-sided Hausdorff distance is the adequate measure for the error of the approximation, when the intended usage is clearance checks, continuous collision detection and maintainability analysis in CAD. We present two implementations that apply the concept and generate a manifold triangle mesh that approximates the outer boundary of a swept volume. Both algorithms are two-phased: a sweeping phase which generates a conservative voxelization of the swept volume, and the actual mesh generation which is based on restricted Delaunay refinement. This approach ensures a high precision of the approximation while respecting conservativeness.rnThe benchmarks for our test are amongst others real world scenarios that come from the automotive industry.rnFurther, we introduce a method to relate parts of an already computed swept volume boundary to those triangles of the generator, that come closest during the sweep. We use this to verify as well as to colorize meshes resulting from our implementations.

Bei technischen Designprozessen in der Automobilindustrie kommen vermehrt digitale Prototypen zum Einsatz um anhand von CAD-Modellen frühzeitig zu Fehler zu erkennen. Darunter fallen auch Bauraum- und Wartbarkeitsuntersuchungen durch die Berechnung des überstrichenen Volumens (Swept Volumes).rnDas Swept Volume ist beispielsweise sehr hilfreich, um Problemzonen zu identifizieren, in denen eine Unterschreitung von einzuhaltenden Sicherheitsabständen droht. Durch die explizite Konstruktion des Swept Volumes erhält der Ingenieur klare Hinweise darauf, wie die Form von Bauteilen, die sich zu nahe kommen, zu modifizieren ist. In dieser Arbeit wird zunächst ein Konzept erarbeitet, das der Approximation des äußeren Randes eines von einem Generator überstrichenen Volumens dient. Es ist hierbei aufgrund von Sicherheitsaspekten unerlässlich, dass die Approximation konservativ ist, das eigentliche Volumen also komplett umschlossen wird. Auf der anderen Seite möchte man den maximalen Fehler der Approximation möglichst klein halten, also eine möglichst hohe Präzision erreichen. Es wird in dieser Arbeit gezeigt, dass…

Subjects/Keywords: Swept Volume; Wartbarkeitsuntersuchungen; Bewegungsüllen; Bauraumuntersuchungen; Sicherheitsabstände; CAD; Swept Volume; Maintainability Analysis; Safety Analysis; CAD; Data processing Computer science

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Dziegielewski, A. v. (2012). High precision swept volume approximation with conservative error bounds. (Doctoral Dissertation). Johannes Gutenberg Universität Mainz. Retrieved from http://ubm.opus.hbz-nrw.de/volltexte/2012/3267/

Chicago Manual of Style (16^th Edition):

Dziegielewski, Andreas von. “High precision swept volume approximation with conservative error bounds.” 2012. Doctoral Dissertation, Johannes Gutenberg Universität Mainz. Accessed January 25, 2021. http://ubm.opus.hbz-nrw.de/volltexte/2012/3267/.

MLA Handbook (7^th Edition):

Dziegielewski, Andreas von. “High precision swept volume approximation with conservative error bounds.” 2012. Web. 25 Jan 2021.

Vancouver:

Dziegielewski Av. High precision swept volume approximation with conservative error bounds. [Internet] [Doctoral dissertation]. Johannes Gutenberg Universität Mainz; 2012. [cited 2021 Jan 25]. Available from: http://ubm.opus.hbz-nrw.de/volltexte/2012/3267/.

Council of Science Editors:

Dziegielewski Av. High precision swept volume approximation with conservative error bounds. [Doctoral Dissertation]. Johannes Gutenberg Universität Mainz; 2012. Available from: http://ubm.opus.hbz-nrw.de/volltexte/2012/3267/

North Carolina State University

3. Roberts, David William. The Aerodynamic Analysis and Aeroelastic Tailoring of a Forward-Swept Wing.

Degree: MS, Aerospace Engineering, 2006, North Carolina State University

URL: http://www.lib.ncsu.edu/resolver/1840.16/2141

► The use of forward-swept wings has aerodynamic benefits at high angles of attack and in supersonic regimes. These consist of reduction in wave drag, profile… (more)

Subjects/Keywords: Aeroelastic; Forward-Swept; Divergence

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APA (6^th Edition):

Roberts, D. W. (2006). The Aerodynamic Analysis and Aeroelastic Tailoring of a Forward-Swept Wing. (Thesis). North Carolina State University. Retrieved from http://www.lib.ncsu.edu/resolver/1840.16/2141

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Roberts, David William. “The Aerodynamic Analysis and Aeroelastic Tailoring of a Forward-Swept Wing.” 2006. Thesis, North Carolina State University. Accessed January 25, 2021. http://www.lib.ncsu.edu/resolver/1840.16/2141.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Roberts, David William. “The Aerodynamic Analysis and Aeroelastic Tailoring of a Forward-Swept Wing.” 2006. Web. 25 Jan 2021.

Vancouver:

Roberts DW. The Aerodynamic Analysis and Aeroelastic Tailoring of a Forward-Swept Wing. [Internet] [Thesis]. North Carolina State University; 2006. [cited 2021 Jan 25]. Available from: http://www.lib.ncsu.edu/resolver/1840.16/2141.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Roberts DW. The Aerodynamic Analysis and Aeroelastic Tailoring of a Forward-Swept Wing. [Thesis]. North Carolina State University; 2006. Available from: http://www.lib.ncsu.edu/resolver/1840.16/2141

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Miami

4. Mihajloski, Todor. Swept - Tone Evoked Otoacoustic Emissions: Stimulus Calibration and Equalization.

Degree: MS, Biomedical Engineering (Engineering), 2011, University of Miami

URL: https://scholarlyrepository.miami.edu/oa_theses/301

► Otoacoustic Emissions (OAE) are minute acoustic responses originating from the cochlea as a result of an external acoustic stimulus and are recorded using a sensitive… (more)

Subjects/Keywords: Otoacoustic Emissions; OAE; Swept-Tone; Hearing Level; DSP; Signal Processing

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Mihajloski, T. (2011). Swept - Tone Evoked Otoacoustic Emissions: Stimulus Calibration and Equalization. (Thesis). University of Miami. Retrieved from https://scholarlyrepository.miami.edu/oa_theses/301

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Mihajloski, Todor. “Swept - Tone Evoked Otoacoustic Emissions: Stimulus Calibration and Equalization.” 2011. Thesis, University of Miami. Accessed January 25, 2021. https://scholarlyrepository.miami.edu/oa_theses/301.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Mihajloski, Todor. “Swept - Tone Evoked Otoacoustic Emissions: Stimulus Calibration and Equalization.” 2011. Web. 25 Jan 2021.

Vancouver:

Mihajloski T. Swept - Tone Evoked Otoacoustic Emissions: Stimulus Calibration and Equalization. [Internet] [Thesis]. University of Miami; 2011. [cited 2021 Jan 25]. Available from: https://scholarlyrepository.miami.edu/oa_theses/301.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Mihajloski T. Swept - Tone Evoked Otoacoustic Emissions: Stimulus Calibration and Equalization. [Thesis]. University of Miami; 2011. Available from: https://scholarlyrepository.miami.edu/oa_theses/301

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Delft University of Technology

5. Sol, M.B. (author). Conceptual Design of Swept Wing Root Aerofoils.

Degree: 2015, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:5bf482f6-5910-4346-abd5-785748980bc9

► For modern transonic transport aeroplanes, it is important to produce low drag at high cruise speeds. The root effect, caused by effects of symmetry on… (more)

▼ For modern transonic transport aeroplanes, it is important to produce low drag at high cruise speeds. The root effect, caused by effects of symmetry on swept wings, decreases the performance of these aeroplanes. During aeroplane design, root modifications are applied to counteract this decrease in performance. Most conceptual aeroplane design tools do not have a method for design of the root aerofoil. However, the design of the root aerofoil has a significant influence on the properties of the final design, since it transfers the loads from the wing to the fuselage. Therefore, having a conceptual method for design of the wing root aerofoil will increase the accuracy of a conceptual aeroplane design. For conceptual design, computational times are important, to allow the designer to try different approaches and get a feel for the design. In this report a method is developed to approximate the root aerofoil design to achieve straight isobars on a wing of any given shape, within computational times that are suitable for conceptual design. First a method is developed for estimating the pressure distribution over the root aerofoil of a given wing. This is done by combining a method for estimation of the root effect due to thickness, a method for estimation of the root effect due to lift, a Vortex Lattice Method (VLM) and a two-dimensional panel method. A full potential method, MATRICS-V, is used to verify the results of the method, because of its proven validity. It is shown that the results of the first part of the method are generally in good agreement with results found by MATRICS-V. The effects of wing sweep, wing taper and addition of a wing kink can be modelled with results that are in good agreement with the verification data. For aft swept wings with positive lift, the pressure near the leading edge is underestimated. For forward swept wings with positive lift, the pressure on the upper surface is overestimated. For wings with a cambered aerofoil an inaccuracy occurs over the forward part of the profile. The general shape of the curve, however, is captured. Secondly, this method is coupled with an optimisation method for the root aerofoil, using Class-Shape function Transformation (CST) parametrisation. The target of the optimisation is set to achieve a similar pressure distribution over the wing root aerofoil as the pressure distribution over the outboard section of the wing. For the developed method, it is difficult to show that the results are valid, since there is no method that has a one-to-one match with the method developed. Therefore, the results are compared to the general characteristics observed in actual root aerofoil designs. The method shows the characteristic behaviour in terms of change in camber, change in location of maximumthickness and change in incidence angle. The increase in thickness, however, is not present. This is caused by the fact that the lower surface pressure distribution is also set as a target. In actual aeroplane design the lower surface is of less importance. In the method… Advisors/Committee Members: Vos, R. (mentor).

Subjects/Keywords: conceptual; design; swept wing; wing root; aerofoil; straight isobars

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Sol, M. B. (. (2015). Conceptual Design of Swept Wing Root Aerofoils. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:5bf482f6-5910-4346-abd5-785748980bc9

Chicago Manual of Style (16^th Edition):

Sol, M B (author). “Conceptual Design of Swept Wing Root Aerofoils.” 2015. Masters Thesis, Delft University of Technology. Accessed January 25, 2021. http://resolver.tudelft.nl/uuid:5bf482f6-5910-4346-abd5-785748980bc9.

MLA Handbook (7^th Edition):

Sol, M B (author). “Conceptual Design of Swept Wing Root Aerofoils.” 2015. Web. 25 Jan 2021.

Vancouver:

Sol MB(. Conceptual Design of Swept Wing Root Aerofoils. [Internet] [Masters thesis]. Delft University of Technology; 2015. [cited 2021 Jan 25]. Available from: http://resolver.tudelft.nl/uuid:5bf482f6-5910-4346-abd5-785748980bc9.

Council of Science Editors:

Sol MB(. Conceptual Design of Swept Wing Root Aerofoils. [Masters Thesis]. Delft University of Technology; 2015. Available from: http://resolver.tudelft.nl/uuid:5bf482f6-5910-4346-abd5-785748980bc9

Delft University of Technology

6. Munaro, Filippo (author). Mechanisms of boundary layer transition due to isolated roughness on swept wings: An experimental study.

Degree: 2017, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:bf38047c-96ea-4090-8d1a-9e5760e3f9d3

► In the context of the ongoing research regarding boundary layer transition, this project aims to study the effects of isolated cylindrical roughness elements on the… (more)

▼ In the context of the ongoing research regarding boundary layer transition, this project aims to study the effects of isolated cylindrical roughness elements on the transition from laminar to turbulent flow in a swept wing boundary layer. The project entails experimental campaigns: the 45 degrees swept wing model is placed inside the test section of the Low Turbulence Tunnel (LTT) and millimeter-sized roughness elements are attached to it, so that their interference with the boundary layer flow can be studied. The main goal is to investigate the flow features generating aft the roughness elements and their development into turbulent streaks. Moreover, this project aims to understand and quantify the effects of different roughness sizes on transition mechanisms, in the specific case of a three-dimensional boundary layer. This is achieved by means of different experimental techniques, such as PIV, HWA and thermographic flow visualization. The obtained results lead to a comprehensive description of this type of flows, with several phenomena changing their characteristics due to a change in parameters (freestream speed, roughness diameter and roughness height). Velocity field, spectral analysis of the signal, wedge width evolution, instability modes and velocity fluctuations in time were investigated with different parametric conditions, in order to understand how the flow was affected by them. Furthermore, the study allowed to evaluate the use of non-dimensional parameters such as roughness Reynolds number and aspect ratio for the prediction of the flow topology. The complexity of the phenomena involved is underlined in the conclusions of this research, with the interaction of several flow features making it a broad and interdisciplinary field of research. Advisors/Committee Members: Kotsonis, Marios (mentor), Serpieri, Jacopo (mentor), Scarano, Fulvio (graduation committee), Ye, Qingqing (graduation committee), Avallone, Francesco (graduation committee), Delft University of Technology (degree granting institution).

Subjects/Keywords: Aerodynamics; Transition; Boundary Layer; Swept Wing; Wind Tunnel; Isolated Roughness

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APA (6^th Edition):

Munaro, F. (. (2017). Mechanisms of boundary layer transition due to isolated roughness on swept wings: An experimental study. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:bf38047c-96ea-4090-8d1a-9e5760e3f9d3

Chicago Manual of Style (16^th Edition):

Munaro, Filippo (author). “Mechanisms of boundary layer transition due to isolated roughness on swept wings: An experimental study.” 2017. Masters Thesis, Delft University of Technology. Accessed January 25, 2021. http://resolver.tudelft.nl/uuid:bf38047c-96ea-4090-8d1a-9e5760e3f9d3.

MLA Handbook (7^th Edition):

Munaro, Filippo (author). “Mechanisms of boundary layer transition due to isolated roughness on swept wings: An experimental study.” 2017. Web. 25 Jan 2021.

Vancouver:

Munaro F(. Mechanisms of boundary layer transition due to isolated roughness on swept wings: An experimental study. [Internet] [Masters thesis]. Delft University of Technology; 2017. [cited 2021 Jan 25]. Available from: http://resolver.tudelft.nl/uuid:bf38047c-96ea-4090-8d1a-9e5760e3f9d3.

Council of Science Editors:

Munaro F(. Mechanisms of boundary layer transition due to isolated roughness on swept wings: An experimental study. [Masters Thesis]. Delft University of Technology; 2017. Available from: http://resolver.tudelft.nl/uuid:bf38047c-96ea-4090-8d1a-9e5760e3f9d3

University of Washington

7. Yoshida, William Tsuyoshi. Investigation of the Flowfield Downstream of a Discontinuous Backward-Facing Step on a Swept Flat Plate.

Degree: 2020, University of Washington

URL: http://hdl.handle.net/1773/46362

► An experimental study of a swept flat plate has been performed in the University of Washington 3’ by 3’ Low-Speed Wind Tunnel to improve the… (more)

▼ An experimental study of a swept flat plate has been performed in the University of Washington 3’ by 3’ Low-Speed Wind Tunnel to improve the understanding of iced swept-wing flowfields. The swept flat plate model included two interchangeable backward-facing steps that were mounted to the full span of the plate leading edge, as well as an adjustable trailing-edge flap. Each of the steps was designed to recreate one of two key flowfields characteristic of swept-wing artificial ice shapes while reducing the geometric complexity of the swept wing model. The first was a spanwise-running leading-edge vortex produced by certain low-fidelity artificial ice shapes. This type of flowfield is referred to as Type I, and was produced using the solid backward-facing step. Characteristic streamwise-running streaks of oil identify the second flowfield in surface flow visualization. This flow pattern was referred to as Type II, and was recreated with a modified backward-facing step that included spanwise-periodic gaps and solid features. Configurations of the flat plate were tested at four trailing-edge flap settings, and three Reynolds numbers based on step height of 2.50Ã 104, 3.78Ã 104, and 5.03Ã 104, which correspond to Mach numbers of0.088, 0.132, and 0.176. The experimental techniques used included fluorescent-oil surface flow visualization, surface pressure measurements, and five-hole pressure probe measurements. From measurements made using a five-hole pressure probe, it was shown that the trailing-edge flap had significant effects on the local flow angularity about the leading-edge. These angularity changes varied across the span and had visible effects on the resulting oil flow visualization. Type II streamwise flow features were identified as having one of two sets of traits using two oil flow visualization techniques, For configurations with negative flap deflection, the flowfield behind the step was dominated by clear streamwise streaks, each appearing to emanate from a gap in the step. A detailed surface oil flow visualization technique presented evidence that this type of streamwise feature may be the result of pairs of counter-rotating streamwise vortices that form in the wake behind each solid feature in the step. This composition was distinct from the second type, which was seen at high flap angles in the oil flow as a superposition of a leading-edge separation vortex and streamwise streaks of vortical flow. These streaks were larger than the first case, and did not correspond to any single gap or solid feature. This behavior is similar to the flowfields associated with certain low-fidelity representations of scallop artificial ice shapes. The second type was hypothesized to be a result of a streamwise instability in the separated shear layer; however, additional work is required. A coating of 24 grit on the solid step produced small effects in the pressure distribution and tended to increase the mean shear layer reattachment length behind the step. Finally, the effect of Reynolds and Mach number was seen to be… Advisors/Committee Members: Bragg, Michael B (advisor).

Subjects/Keywords: Backward-facing step; Icing; Swept; Aerospace engineering; Aeronautics and astronautics

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Yoshida, W. T. (2020). Investigation of the Flowfield Downstream of a Discontinuous Backward-Facing Step on a Swept Flat Plate. (Thesis). University of Washington. Retrieved from http://hdl.handle.net/1773/46362

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Yoshida, William Tsuyoshi. “Investigation of the Flowfield Downstream of a Discontinuous Backward-Facing Step on a Swept Flat Plate.” 2020. Thesis, University of Washington. Accessed January 25, 2021. http://hdl.handle.net/1773/46362.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Yoshida, William Tsuyoshi. “Investigation of the Flowfield Downstream of a Discontinuous Backward-Facing Step on a Swept Flat Plate.” 2020. Web. 25 Jan 2021.

Vancouver:

Yoshida WT. Investigation of the Flowfield Downstream of a Discontinuous Backward-Facing Step on a Swept Flat Plate. [Internet] [Thesis]. University of Washington; 2020. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1773/46362.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Yoshida WT. Investigation of the Flowfield Downstream of a Discontinuous Backward-Facing Step on a Swept Flat Plate. [Thesis]. University of Washington; 2020. Available from: http://hdl.handle.net/1773/46362

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Arizona

8. Gluck, Jeffrey Weston. Water Tunnel Experiments on Span-wise Variation of Laminar Separation Bubbles for Swept and Unswept Wings using Particle Image Velocimetry .

Degree: 2016, University of Arizona

URL: http://hdl.handle.net/10150/621851

► An inverted airfoil mounted above a flat plate was used to create laminar separation bubbles on a flat plate in water tunnel experiments at low… (more)

▼ An inverted airfoil mounted above a flat plate was used to create laminar separation bubbles on a flat plate in water tunnel experiments at low Reynolds numbers. Boundary layer suction ensured that the flow remained attached to the wing. Two-dimensional PIV measurements were used to qualitatively and quantitatively characterize the spanwise bubble variation on an unswept wing and on the same wing featuring a 22 degree sweep. The separation bubbles were recorded at varied span-wise locations in a 31.5 cm wide region of the flow. The limitations of this measurement region were dictated by the focal length of the laser optic used for PIV measurements. The straight wing exhibited approximately uniform time averaged separation positions across the span of the wing. The reattachment locations varied only slightly which was expected due to the transition to turbulent flow before reattachment. A form of bubble "breathing" was observed in the laminar separation bubbles on the straight wing and is believed to have affected the mean reattachment locations for two data points recorded. The shedding frequencies on the straight wing were slightly higher than those obtained from CFD simulations. The swept wing planform showed significantly more variation in the mean separation and reattachment locations with respect to the leading edge of the wing. There is a general trend of the separation locations moving upstream in the direction of the aft leading edge. The reattachment points are shown to move downstream as the separation points move upstream relative to the leading edge and visa versa, displaying an inverse relationship between the two. The bubble lengths were found to be slightly longer on the swept wing compared to the straight wing usually by about 10%. The shedding frequencies on the swept wing were found to be lower than the straight wing. The quality of flow in the water tunnel may have degraded over time, showing signs of increased free stream turbulence. After data collection, it was also discovered that the boundary layer suction on the wing was not constant at all span-wise locations. It is believed that the introduction of wing sweep intensified the effect of insufficient suction on the structure of the bubbles observed. The present results were in agreement with previous research for bubble structure but the dynamic instabilities were found to differ slightly. Advisors/Committee Members: Fasel, Hermann (advisor), Little, Jesse (committeemember), Kerschen, Edward (committeemember).

Subjects/Keywords: Swept; Unswept; Water Tunnel; Wing; Aerospace Engineering; PIV

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Gluck, J. W. (2016). Water Tunnel Experiments on Span-wise Variation of Laminar Separation Bubbles for Swept and Unswept Wings using Particle Image Velocimetry . (Masters Thesis). University of Arizona. Retrieved from http://hdl.handle.net/10150/621851

Chicago Manual of Style (16^th Edition):

Gluck, Jeffrey Weston. “Water Tunnel Experiments on Span-wise Variation of Laminar Separation Bubbles for Swept and Unswept Wings using Particle Image Velocimetry .” 2016. Masters Thesis, University of Arizona. Accessed January 25, 2021. http://hdl.handle.net/10150/621851.

MLA Handbook (7^th Edition):

Gluck, Jeffrey Weston. “Water Tunnel Experiments on Span-wise Variation of Laminar Separation Bubbles for Swept and Unswept Wings using Particle Image Velocimetry .” 2016. Web. 25 Jan 2021.

Vancouver:

Gluck JW. Water Tunnel Experiments on Span-wise Variation of Laminar Separation Bubbles for Swept and Unswept Wings using Particle Image Velocimetry . [Internet] [Masters thesis]. University of Arizona; 2016. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/10150/621851.

Council of Science Editors:

Gluck JW. Water Tunnel Experiments on Span-wise Variation of Laminar Separation Bubbles for Swept and Unswept Wings using Particle Image Velocimetry . [Masters Thesis]. University of Arizona; 2016. Available from: http://hdl.handle.net/10150/621851

University of Arizona

9. Yamauchi, Atsushi. Limitations of Reynolds Averaging in Forced Skewed Turbulent Mixing Layer .

Degree: 2019, University of Arizona

URL: http://hdl.handle.net/10150/636915

► An experimental investigation aimed at studying the three-dimensional character of a turbulent mixing layer created downstream of a swept-back wing that served as a splitter… (more)

▼ An experimental investigation aimed at studying the three-dimensional character of a turbulent mixing layer created downstream of a swept-back wing that served as a splitter plate and a screen that reduced the velocity in the test section on the lower side of the wing has been undertaken. The sweptback of the wing and the screen was 45o.The potential for the controllability of this flow was also evaluated by using spanwise uniform periodic excitation in order to assess the sensitivity of the flow to oblique imposed perturbations. The previous experiment (Suehiro (2017)) using splitter plate with the trailing edge having a “Λ” shape showed the complicated pattern of interacting waves emanating from both sides of the “Λ” notch. In order to investigate only one-sided effect which is simpler because of the absence of these interferences, the skewed swept-back wing was used for this research. Mean velocities measured by an array of pitot tubes, instantaneous velocities measured by PIV, and the hotwire data for spectrum analysis were taken to analyze the mixing layer. The velocity profiles with forcing frequency of 50Hz attained self-similarities whereas that with forcing frequency of 75Hz was distorted and they were not self-similar. Traditionally the center of the mixing layer is arbitrarily defined as the location where the velocity is the average of the two streams. Forcing the mixing layer at a frequency of 50Hz generated only minor distortions to the sinusoidal oscillation of the mixing layer center while forcing 75Hz distorted the center much more. The mixing layer with forcing frequency of 75Hz where the amplitude of the oscillations was 1.5mm was too amplified. As a result of the excessive amplification, there were two regimes. The flow experienced those regimes in time and in space. That is why a single scale length scale such as the vorticity thickness or the momentum thickness cannot be used to scale width of the turbulent mixing layer at all times and locations. Advisors/Committee Members: Wygnanski, Israel J (advisor), Little, Jesse C. (committeemember), Tumin, Anatoli (committeemember).

Subjects/Keywords: Mixing layer; Reynolds Averaging; Skewed Turbulent Mixing; Swept-back Wing

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APA (6^th Edition):

Yamauchi, A. (2019). Limitations of Reynolds Averaging in Forced Skewed Turbulent Mixing Layer . (Masters Thesis). University of Arizona. Retrieved from http://hdl.handle.net/10150/636915

Chicago Manual of Style (16^th Edition):

Yamauchi, Atsushi. “Limitations of Reynolds Averaging in Forced Skewed Turbulent Mixing Layer .” 2019. Masters Thesis, University of Arizona. Accessed January 25, 2021. http://hdl.handle.net/10150/636915.

MLA Handbook (7^th Edition):

Yamauchi, Atsushi. “Limitations of Reynolds Averaging in Forced Skewed Turbulent Mixing Layer .” 2019. Web. 25 Jan 2021.

Vancouver:

Yamauchi A. Limitations of Reynolds Averaging in Forced Skewed Turbulent Mixing Layer . [Internet] [Masters thesis]. University of Arizona; 2019. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/10150/636915.

Council of Science Editors:

Yamauchi A. Limitations of Reynolds Averaging in Forced Skewed Turbulent Mixing Layer . [Masters Thesis]. University of Arizona; 2019. Available from: http://hdl.handle.net/10150/636915

Cal Poly

10. Egorov, Jacob. Wavelength accuracy study for high-density Fiber Bragg grating sensor systems using a Rapidly-Swept Akinetic-Laser source.

Degree: MS, Electrical Engineering, 2016, Cal Poly

URL: https://digitalcommons.calpoly.edu/theses/1654 ; 10.15368/theses.2016.113

► This thesis studies the center wavelength accuracy of a Fiber Bragg Grating Sensor system that has a large number of sensor elements both as… (more)

▼ This thesis studies the center wavelength accuracy of a Fiber Bragg Grating Sensor system that has a large number of sensor elements both as a function of wavelength and as a function of position. Determining the center wavelength of each of the fiber optic sensors is a critical parameter that ultimately determines sensor accuracy. The high density environment can result in degradation of accuracy of the center wavelength measurement. This thesis aims to quantify this measurement error both with theoretical and experimental studies. There are many sensing applications where optical fiber sensors are preferred over electrical sensors, such as the oil and gas industry where fiber optic sensors are used to monitor wells and pipelines due to their low signal degradation over long distances and immunity to harsh physical environments. Fiber Bragg grating (FBG) sensors in particular have widespread use because of their versatility, measurement sensitivity, and distributed multiplexing abilities. In conventional wavelength multiplexing, up to 50 FBG sensors are spread out over a band of 100nm, each with a center wavelength difference large enough so that each element can be individually measured. However, numerous sensing applications require several hundred to over a thousand sensors cascaded together on a single fiber. These sensor arrays use a combination of WDM and TDM for measurements, where many FBG sensors with the same center wavelength are separated by a long enough length of fiber so that the reflected signals are separated in time. These Wavelength-to-Time Domain Multiplexing (W-TDM) measurements are enabled by Insight Photonic’s new ‘akinetically’ swept, all-semiconductor laser. This laser is a Vernier-Tuned Distributed Bragg Reflector (VT-DBR) device, capable of rapidly sweeping through different wavelengths without any moving parts. Attributes that make this laser superior to mechanically-swept lasers include: 1) short and long term consistent sweep-sweep reliability, 2) availability at many wavelengths, 3) a narrow linewidth with single longitudinal mode, and 4) the ability to do non-traditional sweep patterns that facilitate measurement of high-density sensor networks. In this thesis, experiments will be performed in the lab with the Insight VT-DBR laser to determine how accurately the center wavelength of a single Fiber Bragg grating can be measured. Experiments will also be performed with two and three FBGs to compare different algorithmic approaches to measurements. The second part of the thesis will simulate both single and multiple FBG sensor environments, comparing the center wavelength measurement accuracy results for different parameters including signal-to-noise ratios, wavelength point density, FBG loss and width, and multiple algorithmic approaches. The results of these experiments and simulations will demonstrate how accurate a FBG sensor system is at particular parameters, which will be useful to those designing a sensor network or performing similar experiments. Advisors/Committee Members: Dr. Dennis Derickson.

Subjects/Keywords: photonics; laser; optics; fiber; bragg grating; swept; Electromagnetics and Photonics

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APA (6^th Edition):

Egorov, J. (2016). Wavelength accuracy study for high-density Fiber Bragg grating sensor systems using a Rapidly-Swept Akinetic-Laser source. (Masters Thesis). Cal Poly. Retrieved from https://digitalcommons.calpoly.edu/theses/1654 ; 10.15368/theses.2016.113

Chicago Manual of Style (16^th Edition):

Egorov, Jacob. “Wavelength accuracy study for high-density Fiber Bragg grating sensor systems using a Rapidly-Swept Akinetic-Laser source.” 2016. Masters Thesis, Cal Poly. Accessed January 25, 2021. https://digitalcommons.calpoly.edu/theses/1654 ; 10.15368/theses.2016.113.

MLA Handbook (7^th Edition):

Egorov, Jacob. “Wavelength accuracy study for high-density Fiber Bragg grating sensor systems using a Rapidly-Swept Akinetic-Laser source.” 2016. Web. 25 Jan 2021.

Vancouver:

Egorov J. Wavelength accuracy study for high-density Fiber Bragg grating sensor systems using a Rapidly-Swept Akinetic-Laser source. [Internet] [Masters thesis]. Cal Poly; 2016. [cited 2021 Jan 25]. Available from: https://digitalcommons.calpoly.edu/theses/1654 ; 10.15368/theses.2016.113.

Council of Science Editors:

Egorov J. Wavelength accuracy study for high-density Fiber Bragg grating sensor systems using a Rapidly-Swept Akinetic-Laser source. [Masters Thesis]. Cal Poly; 2016. Available from: https://digitalcommons.calpoly.edu/theses/1654 ; 10.15368/theses.2016.113

Georgia Tech

11. Rowe, William Thomas. Analysis of wind-tunnel investigations of trailing-edge flaps on swept-back wings.

Degree: MS, Aeronautical Engineering, 1950, Georgia Tech

URL: http://hdl.handle.net/1853/11967

Subjects/Keywords: Aerodynamics; Airplanes Wings, Swept-back

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APA (6^th Edition):

Rowe, W. T. (1950). Analysis of wind-tunnel investigations of trailing-edge flaps on swept-back wings. (Masters Thesis). Georgia Tech. Retrieved from http://hdl.handle.net/1853/11967

Chicago Manual of Style (16^th Edition):

Rowe, William Thomas. “Analysis of wind-tunnel investigations of trailing-edge flaps on swept-back wings.” 1950. Masters Thesis, Georgia Tech. Accessed January 25, 2021. http://hdl.handle.net/1853/11967.

MLA Handbook (7^th Edition):

Rowe, William Thomas. “Analysis of wind-tunnel investigations of trailing-edge flaps on swept-back wings.” 1950. Web. 25 Jan 2021.

Vancouver:

Rowe WT. Analysis of wind-tunnel investigations of trailing-edge flaps on swept-back wings. [Internet] [Masters thesis]. Georgia Tech; 1950. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1853/11967.

Council of Science Editors:

Rowe WT. Analysis of wind-tunnel investigations of trailing-edge flaps on swept-back wings. [Masters Thesis]. Georgia Tech; 1950. Available from: http://hdl.handle.net/1853/11967

Georgia Tech

12. Eason, William Myron. An investigation of sweptback wing root stresses.

Degree: MS, Aeronautical Engineering, 1955, Georgia Tech

URL: http://hdl.handle.net/1853/12330

Subjects/Keywords: Airplanes Wings; Swept-back

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APA (6^th Edition):

Eason, W. M. (1955). An investigation of sweptback wing root stresses. (Masters Thesis). Georgia Tech. Retrieved from http://hdl.handle.net/1853/12330

Chicago Manual of Style (16^th Edition):

Eason, William Myron. “An investigation of sweptback wing root stresses.” 1955. Masters Thesis, Georgia Tech. Accessed January 25, 2021. http://hdl.handle.net/1853/12330.

MLA Handbook (7^th Edition):

Eason, William Myron. “An investigation of sweptback wing root stresses.” 1955. Web. 25 Jan 2021.

Vancouver:

Eason WM. An investigation of sweptback wing root stresses. [Internet] [Masters thesis]. Georgia Tech; 1955. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1853/12330.

Council of Science Editors:

Eason WM. An investigation of sweptback wing root stresses. [Masters Thesis]. Georgia Tech; 1955. Available from: http://hdl.handle.net/1853/12330

Georgia Tech

13. Powers, Sidney Alan. The effect of the ground plane on low aspect ratio swept wings.

Degree: MS, Aeronautical Engineering, 1955, Georgia Tech

URL: http://hdl.handle.net/1853/13073

Subjects/Keywords: Airplanes Wings; Swept-back

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APA (6^th Edition):

Powers, S. A. (1955). The effect of the ground plane on low aspect ratio swept wings. (Masters Thesis). Georgia Tech. Retrieved from http://hdl.handle.net/1853/13073

Chicago Manual of Style (16^th Edition):

Powers, Sidney Alan. “The effect of the ground plane on low aspect ratio swept wings.” 1955. Masters Thesis, Georgia Tech. Accessed January 25, 2021. http://hdl.handle.net/1853/13073.

MLA Handbook (7^th Edition):

Powers, Sidney Alan. “The effect of the ground plane on low aspect ratio swept wings.” 1955. Web. 25 Jan 2021.

Vancouver:

Powers SA. The effect of the ground plane on low aspect ratio swept wings. [Internet] [Masters thesis]. Georgia Tech; 1955. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1853/13073.

Council of Science Editors:

Powers SA. The effect of the ground plane on low aspect ratio swept wings. [Masters Thesis]. Georgia Tech; 1955. Available from: http://hdl.handle.net/1853/13073

Lehigh University

14. Rumbaugh, Jr., Douglas Bahr. A Design Proposal for a Novel Gun-Launched Unmanned Aerial System.

Degree: MS, Mechanical Engineering, 2018, Lehigh University

URL: https://preserve.lehigh.edu/etd/4318

► A proposed design for a gun-launched, unmanned aerial system (GLUAS) is presented, along with experimental data pertaining to the characterization of said design, and specifically… (more)

Subjects/Keywords: flexibility; MAV; steady flow; swept wing; UAS; UAV; Mechanical Engineering

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APA (6^th Edition):

Rumbaugh, Jr., D. B. (2018). A Design Proposal for a Novel Gun-Launched Unmanned Aerial System. (Thesis). Lehigh University. Retrieved from https://preserve.lehigh.edu/etd/4318

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Rumbaugh, Jr., Douglas Bahr. “A Design Proposal for a Novel Gun-Launched Unmanned Aerial System.” 2018. Thesis, Lehigh University. Accessed January 25, 2021. https://preserve.lehigh.edu/etd/4318.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Rumbaugh, Jr., Douglas Bahr. “A Design Proposal for a Novel Gun-Launched Unmanned Aerial System.” 2018. Web. 25 Jan 2021.

Vancouver:

Rumbaugh, Jr. DB. A Design Proposal for a Novel Gun-Launched Unmanned Aerial System. [Internet] [Thesis]. Lehigh University; 2018. [cited 2021 Jan 25]. Available from: https://preserve.lehigh.edu/etd/4318.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Rumbaugh, Jr. DB. A Design Proposal for a Novel Gun-Launched Unmanned Aerial System. [Thesis]. Lehigh University; 2018. Available from: https://preserve.lehigh.edu/etd/4318

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Utah State University

15. Reid, Jackson T. A General Approach to Lifting-Line Theory, Applied to Wings with Sweep.

Degree: PhD, Mechanical and Aerospace Engineering, 2020, Utah State University

URL: https://digitalcommons.usu.edu/etd/7842

► Lifting-line theory is one simple method of predicting the lift produced by a wing. The traditional implementation of lifting-line theory, developed in 1918, is… (more)

Subjects/Keywords: Lifting-line theory; swept wings; airfoil; vortex; lift; Aerospace Engineering

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APA (6^th Edition):

Reid, J. T. (2020). A General Approach to Lifting-Line Theory, Applied to Wings with Sweep. (Doctoral Dissertation). Utah State University. Retrieved from https://digitalcommons.usu.edu/etd/7842

Chicago Manual of Style (16^th Edition):

Reid, Jackson T. “A General Approach to Lifting-Line Theory, Applied to Wings with Sweep.” 2020. Doctoral Dissertation, Utah State University. Accessed January 25, 2021. https://digitalcommons.usu.edu/etd/7842.

MLA Handbook (7^th Edition):

Reid, Jackson T. “A General Approach to Lifting-Line Theory, Applied to Wings with Sweep.” 2020. Web. 25 Jan 2021.

Vancouver:

Reid JT. A General Approach to Lifting-Line Theory, Applied to Wings with Sweep. [Internet] [Doctoral dissertation]. Utah State University; 2020. [cited 2021 Jan 25]. Available from: https://digitalcommons.usu.edu/etd/7842.

Council of Science Editors:

Reid JT. A General Approach to Lifting-Line Theory, Applied to Wings with Sweep. [Doctoral Dissertation]. Utah State University; 2020. Available from: https://digitalcommons.usu.edu/etd/7842

16. Diebold, Jeffrey. Aerodynamics of a swept wing with leading-edge ice at low Reynolds number.

Degree: MS, 4048, 2012, University of Illinois – Urbana-Champaign

URL: http://hdl.handle.net/2142/34279

► An experimental study of the aerodynamics of a swept wing with ice at low Reynolds number has been performed. The goal of this work was… (more)

▼ An experimental study of the aerodynamics of a swept wing with ice at low Reynolds number has been performed. The goal of this work was to demonstrate the use of various experimental techniques applied to understanding the aerodynamic effects of a leading-edge ice simulation on a highly swept, high-aspect ratio wing. The swept wing model was a modified version of the NASA Common Research Model, designed to represent a typical wide body commercial airliner. The modified geometry of the model used in this study included a ΛLE = 35º, AR = 8.3 and λ=0.296. The experimental techniques used were force balance measurements, surface pressure measurements, surface oil flow visualization and 5-hole probe wake surveys. Tests were performed at Reynolds numbers of 3x105, 6x105 and 7.8x105 and corresponding Mach numbers of 0.08, 0.15 and 0.2. Force balance results show that the ice shape had a significant effect on performance. The stalling angle of attack and maximum lift coefficient were reduced while the drag was increased throughout the entire range of angles of attack tested. A large leading-edge vortex behind the ice shape was observed in the oil flow, and the pressure measurements showed this vortex had a significant effect on the pressure field over the wing. From the 5-hole wake survey results it was seen that the ice shape increased the profile drag while the induced drag was relatively unaffected. Using the oil flow, the evolution of the leading-edge vortex was observed and features seen in the oil flow were related to features observed in the wake. The flowfield of the iced wing contained several similarities to the flowfield of an airfoil with horn ice; however, there were several important differences due to the three-dimensional nature of the swept wing flowfield. The spanwise distribution of lift and drag were also investigated. By comparing the distributions on the clean and iced wing it was possible to determine that the ice had the largest impact on the aerodynamics of the outboard sections. It was also shown that features observed in the surface oil flow and the wake can be correlated to certain features in the lift and drag distributions. Finally, the effect of the Reynolds number was investigated. Over the range of Reynolds numbers tested, which was not representative of flight, it was observed that the Reynolds number had a reduced influence on the iced wing. This trend was observed in the performance and flowfield results. Advisors/Committee Members: Bragg, Michael B. (advisor).

Subjects/Keywords: aircraft icing; swept wing icing; swept wing aerodynamics

…List of Figures Fig. 2.1 Diagram of swept wing… …20 Fig. 2.3 Lift coefficient distribution of a swept wing. Adapted from Katz… …21 Fig. 2.4 Example of staggered pressure distribution on a swept wing… …29 vii Fig. 2.18 Effect of Reynolds number on the lift of a swept wing with ΛLE= 50º… …35 Fig. 2.29 Ice accretion on a swept wing in glaze icing conditions. Arrows indicate…

11 more images…

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APA (6^th Edition):

Diebold, J. (2012). Aerodynamics of a swept wing with leading-edge ice at low Reynolds number. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/34279

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Diebold, Jeffrey. “Aerodynamics of a swept wing with leading-edge ice at low Reynolds number.” 2012. Thesis, University of Illinois – Urbana-Champaign. Accessed January 25, 2021. http://hdl.handle.net/2142/34279.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Diebold, Jeffrey. “Aerodynamics of a swept wing with leading-edge ice at low Reynolds number.” 2012. Web. 25 Jan 2021.

Vancouver:

Diebold J. Aerodynamics of a swept wing with leading-edge ice at low Reynolds number. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2012. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/2142/34279.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Diebold J. Aerodynamics of a swept wing with leading-edge ice at low Reynolds number. [Thesis]. University of Illinois – Urbana-Champaign; 2012. Available from: http://hdl.handle.net/2142/34279

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

17. Ueda, Naoko. Macular Choroidal Thickness and Volume of Eyes With Reticular Pseudodrusen Using Swept-Source Optical Coherence Tomography : 波長掃引光源型光干渉断層計を用いたreticular pseudodrusen眼の黄斑部脈絡膜厚および体積の検討.

Degree: 博士(医学), 2016, Kyoto University / 京都大学

URL: http://hdl.handle.net/2433/215412 ; http://dx.doi.org/10.14989/doctor.k19586

Final publication is available at http://www.sciencedirect.com/science/article/pii/S0002939414000488

新制・課程博士

甲第19586号

医博第4093号

Subjects/Keywords: reticular pseudodrusen; choroidal thickness; swept-source optical coherence tomography; age-related macular degeneration; drusen

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APA (6^th Edition):

Ueda, N. (2016). Macular Choroidal Thickness and Volume of Eyes With Reticular Pseudodrusen Using Swept-Source Optical Coherence Tomography : 波長掃引光源型光干渉断層計を用いたreticular pseudodrusen眼の黄斑部脈絡膜厚および体積の検討. (Thesis). Kyoto University / 京都大学. Retrieved from http://hdl.handle.net/2433/215412 ; http://dx.doi.org/10.14989/doctor.k19586

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Ueda, Naoko. “Macular Choroidal Thickness and Volume of Eyes With Reticular Pseudodrusen Using Swept-Source Optical Coherence Tomography : 波長掃引光源型光干渉断層計を用いたreticular pseudodrusen眼の黄斑部脈絡膜厚および体積の検討.” 2016. Thesis, Kyoto University / 京都大学. Accessed January 25, 2021. http://hdl.handle.net/2433/215412 ; http://dx.doi.org/10.14989/doctor.k19586.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Ueda, Naoko. “Macular Choroidal Thickness and Volume of Eyes With Reticular Pseudodrusen Using Swept-Source Optical Coherence Tomography : 波長掃引光源型光干渉断層計を用いたreticular pseudodrusen眼の黄斑部脈絡膜厚および体積の検討.” 2016. Web. 25 Jan 2021.

Vancouver:

Ueda N. Macular Choroidal Thickness and Volume of Eyes With Reticular Pseudodrusen Using Swept-Source Optical Coherence Tomography : 波長掃引光源型光干渉断層計を用いたreticular pseudodrusen眼の黄斑部脈絡膜厚および体積の検討. [Internet] [Thesis]. Kyoto University / 京都大学; 2016. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/2433/215412 ; http://dx.doi.org/10.14989/doctor.k19586.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Ueda N. Macular Choroidal Thickness and Volume of Eyes With Reticular Pseudodrusen Using Swept-Source Optical Coherence Tomography : 波長掃引光源型光干渉断層計を用いたreticular pseudodrusen眼の黄斑部脈絡膜厚および体積の検討. [Thesis]. Kyoto University / 京都大学; 2016. Available from: http://hdl.handle.net/2433/215412 ; http://dx.doi.org/10.14989/doctor.k19586

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Alabama

18. Lozes, Brian Andrew. Vibration absorber implementation for space launch vehicle vibration reduction.

Degree: 2010, University of Alabama

URL: http://purl.lib.ua.edu/16198

► Vibration is a major problem in space launch vehicles during burning sequences. These vehicles are vulnerable to impulsive and pulsed vibrations like those produced by… (more)

▼ Vibration is a major problem in space launch vehicles during burning sequences. These vehicles are vulnerable to impulsive and pulsed vibrations like those produced by rocket engines. The Ares I launch vehicle is anticipated to produce vibration in the organ pipe mode. The problems may be particularly severe if the pulses occur at the natural frequencies of the vehicle structure. In the case of the Ares, as the rocket burns, the excitation frequency drifts through the frequency corresponding to a longitudinal mode of the vehicle. Although it is not certain, there is concern that the corresponding vibrations are potentially severe enough as to be lethal to crew members and thus some consideration of vibration mitigation is warranted. Common approaches to dealing with vibration problems - structural redesign, addition of mass or damping materials - are not thought to be viable solutions; structural redesign through addition of mass and/or damping would result in excessive weights with corresponding performance limitations in terms of payload. The alternative approach is to retrofit the aft skirt with one or more tuned vibration absorbers (TVA). Application of an undamped TVA to a primary system introduces a zero in the frequency response of the primary system that is located at the TVA natural frequency. In the case of the Ares, however, the excitation frequency, while easily measured, is not fixed, but varies as the rocket burns. The effect of a TVA on the vibration of a primary system experiencing such an excitation is not known. The main objective of this research was to predict and simulate the behavior of a two degree of freedom (two-mass) system experiencing sinusoidal excitation with a linearly-varying frequency. In doing so, a framework for analyzing a primary system with a TVA implemented was realized. The resulting software was then used to model implementation of a specific TVA solution. Through analytical and simulated solutions, it was confirmed that a specific TVA could be used to effectively absorb the response at target frequencies when acted upon by a linearly changing oscillatory input. (Published By University of Alabama Libraries) Advisors/Committee Members: Williams, Keith A., Baker, John, Haskew, Tim A., University of Alabama. Dept. of Mechanical Engineering.

Subjects/Keywords: Electronic Thesis or Dissertation; – thesis; Engineering, Mechanical; Gliding Tone; Modal Analysis; Swept Input; Vibration

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APA (6^th Edition):

Lozes, B. A. (2010). Vibration absorber implementation for space launch vehicle vibration reduction. (Thesis). University of Alabama. Retrieved from http://purl.lib.ua.edu/16198

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Lozes, Brian Andrew. “Vibration absorber implementation for space launch vehicle vibration reduction.” 2010. Thesis, University of Alabama. Accessed January 25, 2021. http://purl.lib.ua.edu/16198.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Lozes, Brian Andrew. “Vibration absorber implementation for space launch vehicle vibration reduction.” 2010. Web. 25 Jan 2021.

Vancouver:

Lozes BA. Vibration absorber implementation for space launch vehicle vibration reduction. [Internet] [Thesis]. University of Alabama; 2010. [cited 2021 Jan 25]. Available from: http://purl.lib.ua.edu/16198.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Lozes BA. Vibration absorber implementation for space launch vehicle vibration reduction. [Thesis]. University of Alabama; 2010. Available from: http://purl.lib.ua.edu/16198

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Texas A&M University

19. Carbajal, Esteban Franco. Integrating OCT into Surgical Systems and Monitoring Vibrations.

Degree: MS, Biomedical Engineering, 2016, Texas A&M University

URL: http://hdl.handle.net/1969.1/187397

► Imaging of the hearing structures can yield information regarding their function as well as insight into the abnormalities and adverse conditions that affect them. Improvements… (more)

Subjects/Keywords: Optical Coherence Tomography; OCT; Imaging; SSOCT; Swept-Source; Phase; Imaging; 3D Printing

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APA (6^th Edition):

Carbajal, E. F. (2016). Integrating OCT into Surgical Systems and Monitoring Vibrations. (Masters Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/187397

Chicago Manual of Style (16^th Edition):

Carbajal, Esteban Franco. “Integrating OCT into Surgical Systems and Monitoring Vibrations.” 2016. Masters Thesis, Texas A&M University. Accessed January 25, 2021. http://hdl.handle.net/1969.1/187397.

MLA Handbook (7^th Edition):

Carbajal, Esteban Franco. “Integrating OCT into Surgical Systems and Monitoring Vibrations.” 2016. Web. 25 Jan 2021.

Vancouver:

Carbajal EF. Integrating OCT into Surgical Systems and Monitoring Vibrations. [Internet] [Masters thesis]. Texas A&M University; 2016. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1969.1/187397.

Council of Science Editors:

Carbajal EF. Integrating OCT into Surgical Systems and Monitoring Vibrations. [Masters Thesis]. Texas A&M University; 2016. Available from: http://hdl.handle.net/1969.1/187397

Texas A&M University

20. Tofighi Zavareh, Amir. Systems and Methods for the Spectral Calibration of Swept Source Optical Coherence Tomography Systems.

Degree: PhD, Electrical Engineering, 2019, Texas A&M University

URL: http://hdl.handle.net/1969.1/188806

► This dissertation relates to the transition of the state of the art of swept source optical coherence tomography (SS-OCT) systems to a new realm in… (more)

▼ This dissertation relates to the transition of the state of the art of swept source optical coherence tomography (SS-OCT) systems to a new realm in which the image acquisition speed is improved by an order of magnitude. With the aid of a better quality imaging technology, the speed-up factor will considerably shorten the eye-exam clinical visits which in turn improves the patient and doctor interaction experience. These improvements will directly lower associated medical costs for eye-clinics and patients worldwide. There are several other embodiments closely related to Optical Coherence Tomography (OCT) that could benefit from the ideas presented in this dissertation including: optical coherence microscopy (OCM), full-field OCT (FF-OCT), optical coherence elastography (OCE), optical coherence tomography angiography (OCT-A), anatomical OCT (aOCT), optical coherence photoacoustic microscopy (OC-PAM), micro optical coherence tomography (µ OCT), among others. In recent decades, OCT has established itself as the de-facto imaging process that most ophthalmologists refer to in their clinical practices. In a broader sense, optical coherence tomography is used in applications when low penetration and high resolution are desired. These applications include different fields of biomedical sciences including cardiology, dermatology, and pulmonary related sciences. Many other industrial applications including quality control and precise measurements have also been reported that are related to the OCT technology. Every new iteration of OCT technology has always come about with advanced signal processing and data acquisition algorithms using mixed-signal architectures, calibration and signal processing techniques. The existing industrial practices towards data acquisition, processing, and image creation relies on conventional signal processing design flows, which extensively employ continuous/discrete techniques that are both time-consuming and costly. The ideas presented in this dissertation can take the technology to a new dimension of quality of service. Advisors/Committee Members: Hoyos, Sebastian (advisor), Palermo, Samuel (committee member), Braga-Neto, Ulisses (committee member), Biswas, Saurabh (committee member).

Subjects/Keywords: Optical Coherence Tomography; Swept Source Optical Coherence Tomography; Spectral Calibration; Machine Learning; Kalman Filtering

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APA (6^th Edition):

Tofighi Zavareh, A. (2019). Systems and Methods for the Spectral Calibration of Swept Source Optical Coherence Tomography Systems. (Doctoral Dissertation). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/188806

Chicago Manual of Style (16^th Edition):

Tofighi Zavareh, Amir. “Systems and Methods for the Spectral Calibration of Swept Source Optical Coherence Tomography Systems.” 2019. Doctoral Dissertation, Texas A&M University. Accessed January 25, 2021. http://hdl.handle.net/1969.1/188806.

MLA Handbook (7^th Edition):

Tofighi Zavareh, Amir. “Systems and Methods for the Spectral Calibration of Swept Source Optical Coherence Tomography Systems.” 2019. Web. 25 Jan 2021.

Vancouver:

Tofighi Zavareh A. Systems and Methods for the Spectral Calibration of Swept Source Optical Coherence Tomography Systems. [Internet] [Doctoral dissertation]. Texas A&M University; 2019. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1969.1/188806.

Council of Science Editors:

Tofighi Zavareh A. Systems and Methods for the Spectral Calibration of Swept Source Optical Coherence Tomography Systems. [Doctoral Dissertation]. Texas A&M University; 2019. Available from: http://hdl.handle.net/1969.1/188806

University of Toronto

21. Felts Almog, Ilan. Endoscopic Full-Field Swept-Source Optical Coherence Tomography Neuroimaging System.

Degree: 2018, University of Toronto

URL: http://hdl.handle.net/1807/82908

►

Optical Coherence Tomography (OCT) has the capability to differentiate brain elements with intrinsic contrast and at a resolution an order-of-magnitude higher than other imaging modalities.… (more)

Subjects/Keywords: endoscopic; full-field; neuroimaging; optical coherence tomography; stereotactic surgery; swept-source; 0544

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APA (6^th Edition):

Felts Almog, I. (2018). Endoscopic Full-Field Swept-Source Optical Coherence Tomography Neuroimaging System. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/82908

Chicago Manual of Style (16^th Edition):

Felts Almog, Ilan. “Endoscopic Full-Field Swept-Source Optical Coherence Tomography Neuroimaging System.” 2018. Masters Thesis, University of Toronto. Accessed January 25, 2021. http://hdl.handle.net/1807/82908.

MLA Handbook (7^th Edition):

Felts Almog, Ilan. “Endoscopic Full-Field Swept-Source Optical Coherence Tomography Neuroimaging System.” 2018. Web. 25 Jan 2021.

Vancouver:

Felts Almog I. Endoscopic Full-Field Swept-Source Optical Coherence Tomography Neuroimaging System. [Internet] [Masters thesis]. University of Toronto; 2018. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1807/82908.

Council of Science Editors:

Felts Almog I. Endoscopic Full-Field Swept-Source Optical Coherence Tomography Neuroimaging System. [Masters Thesis]. University of Toronto; 2018. Available from: http://hdl.handle.net/1807/82908

University of Washington

22. Sandhu, Navdeep. Aerodynamics of a Swept Wing With Simulated Scalloped Ice at Low Reynolds Number.

Degree: 2018, University of Washington

URL: http://hdl.handle.net/1773/42162

► This thesis studied the aerodynamic effects of a single high-fidelity scalloped ice accretion simulation and a low-fidelity simulation of the same shape. These data were… (more)

Subjects/Keywords: aerodynamics; aircraft icing; CRM65; swept wing; wake survey; Aerospace engineering; Aeronautics and astronautics

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APA (6^th Edition):

Sandhu, N. (2018). Aerodynamics of a Swept Wing With Simulated Scalloped Ice at Low Reynolds Number. (Thesis). University of Washington. Retrieved from http://hdl.handle.net/1773/42162

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Sandhu, Navdeep. “Aerodynamics of a Swept Wing With Simulated Scalloped Ice at Low Reynolds Number.” 2018. Thesis, University of Washington. Accessed January 25, 2021. http://hdl.handle.net/1773/42162.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Sandhu, Navdeep. “Aerodynamics of a Swept Wing With Simulated Scalloped Ice at Low Reynolds Number.” 2018. Web. 25 Jan 2021.

Vancouver:

Sandhu N. Aerodynamics of a Swept Wing With Simulated Scalloped Ice at Low Reynolds Number. [Internet] [Thesis]. University of Washington; 2018. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1773/42162.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Sandhu N. Aerodynamics of a Swept Wing With Simulated Scalloped Ice at Low Reynolds Number. [Thesis]. University of Washington; 2018. Available from: http://hdl.handle.net/1773/42162

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Delft University of Technology

23. Camps Pons, Carlos (author). Experimental investigation of transonic buffet on swept wings: A comparative study between 2D and 3D flow and analysis of sweep angle influence using stereoscopic PIV and Background Oriented Schlieren.

Degree: 2019, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:c1a52829-0267-4211-bf93-109fba0db350

►

Transonic buffet is an aerodynamic instability that appears on aerofoils and wings at certain combinations of Mach number and angle of attack, and which limits… (more)

Subjects/Keywords: Transonic buffet; Swept Wing; Stereoscopic Particle Image Velocimetry (SPIV); Background Oriented Schlieren

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APA (6^th Edition):

Camps Pons, C. (. (2019). Experimental investigation of transonic buffet on swept wings: A comparative study between 2D and 3D flow and analysis of sweep angle influence using stereoscopic PIV and Background Oriented Schlieren. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:c1a52829-0267-4211-bf93-109fba0db350

Chicago Manual of Style (16^th Edition):

Camps Pons, Carlos (author). “Experimental investigation of transonic buffet on swept wings: A comparative study between 2D and 3D flow and analysis of sweep angle influence using stereoscopic PIV and Background Oriented Schlieren.” 2019. Masters Thesis, Delft University of Technology. Accessed January 25, 2021. http://resolver.tudelft.nl/uuid:c1a52829-0267-4211-bf93-109fba0db350.

MLA Handbook (7^th Edition):

Camps Pons, Carlos (author). “Experimental investigation of transonic buffet on swept wings: A comparative study between 2D and 3D flow and analysis of sweep angle influence using stereoscopic PIV and Background Oriented Schlieren.” 2019. Web. 25 Jan 2021.

Vancouver:

Camps Pons C(. Experimental investigation of transonic buffet on swept wings: A comparative study between 2D and 3D flow and analysis of sweep angle influence using stereoscopic PIV and Background Oriented Schlieren. [Internet] [Masters thesis]. Delft University of Technology; 2019. [cited 2021 Jan 25]. Available from: http://resolver.tudelft.nl/uuid:c1a52829-0267-4211-bf93-109fba0db350.

Council of Science Editors:

Camps Pons C(. Experimental investigation of transonic buffet on swept wings: A comparative study between 2D and 3D flow and analysis of sweep angle influence using stereoscopic PIV and Background Oriented Schlieren. [Masters Thesis]. Delft University of Technology; 2019. Available from: http://resolver.tudelft.nl/uuid:c1a52829-0267-4211-bf93-109fba0db350

University of Minnesota

24. Mullen, Michael. Experimental Techniques and Image Reconstruction for Magnetic Resonance Imaging with Inhomogeneous Fields.

Degree: PhD, Physics, 2019, University of Minnesota

URL: http://hdl.handle.net/11299/209115

► Magnetic resonance imaging is quite sensitive to experimental imperfections, necessitating extremely expensive electrical infrastructure and design requirements to permit high-quality experiments to be performed. By… (more)

Subjects/Keywords: frequency-swept pulses; magnetic resonance imaging; multidimensional pulses; parallel imaging; radiofrequency pulses; spatiotemporal

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APA (6^th Edition):

Mullen, M. (2019). Experimental Techniques and Image Reconstruction for Magnetic Resonance Imaging with Inhomogeneous Fields. (Doctoral Dissertation). University of Minnesota. Retrieved from http://hdl.handle.net/11299/209115

Chicago Manual of Style (16^th Edition):

Mullen, Michael. “Experimental Techniques and Image Reconstruction for Magnetic Resonance Imaging with Inhomogeneous Fields.” 2019. Doctoral Dissertation, University of Minnesota. Accessed January 25, 2021. http://hdl.handle.net/11299/209115.

MLA Handbook (7^th Edition):

Mullen, Michael. “Experimental Techniques and Image Reconstruction for Magnetic Resonance Imaging with Inhomogeneous Fields.” 2019. Web. 25 Jan 2021.

Vancouver:

Mullen M. Experimental Techniques and Image Reconstruction for Magnetic Resonance Imaging with Inhomogeneous Fields. [Internet] [Doctoral dissertation]. University of Minnesota; 2019. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/11299/209115.

Council of Science Editors:

Mullen M. Experimental Techniques and Image Reconstruction for Magnetic Resonance Imaging with Inhomogeneous Fields. [Doctoral Dissertation]. University of Minnesota; 2019. Available from: http://hdl.handle.net/11299/209115

University of Arizona

25. Sassu, Matthew George. Software Implementation of a Combined Fluorescence and Swept Source Optical Coherence Tomography Imaging System .

Degree: 2018, University of Arizona

URL: http://hdl.handle.net/10150/631417

► This paper serves as a detailed overview of the software developed for the Falloposcope endoscope being developed by the Jennifer Barton Optics Tissue Laboratory. The… (more)

Subjects/Keywords: AlazarTech; CCD Imaging; C++/CLI; Fluorescence Imaging; SS-OCT; Swept Source Optical Coherence Tomography

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APA (6^th Edition):

Sassu, M. G. (2018). Software Implementation of a Combined Fluorescence and Swept Source Optical Coherence Tomography Imaging System . (Masters Thesis). University of Arizona. Retrieved from http://hdl.handle.net/10150/631417

Chicago Manual of Style (16^th Edition):

Sassu, Matthew George. “Software Implementation of a Combined Fluorescence and Swept Source Optical Coherence Tomography Imaging System .” 2018. Masters Thesis, University of Arizona. Accessed January 25, 2021. http://hdl.handle.net/10150/631417.

MLA Handbook (7^th Edition):

Sassu, Matthew George. “Software Implementation of a Combined Fluorescence and Swept Source Optical Coherence Tomography Imaging System .” 2018. Web. 25 Jan 2021.

Vancouver:

Sassu MG. Software Implementation of a Combined Fluorescence and Swept Source Optical Coherence Tomography Imaging System . [Internet] [Masters thesis]. University of Arizona; 2018. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/10150/631417.

Council of Science Editors:

Sassu MG. Software Implementation of a Combined Fluorescence and Swept Source Optical Coherence Tomography Imaging System . [Masters Thesis]. University of Arizona; 2018. Available from: http://hdl.handle.net/10150/631417

University of Arizona

26. McGee, Oliver Gregory, III. A three dimensional elasticity based solution for free vibrations of simultaneously skewed and twisted cantilever parallelepipeds.

Degree: 1988, University of Arizona

URL: http://hdl.handle.net/10150/184517

► This work is the first 3-D continuum study of the free vibration of skewed and simultaneously skewed and twisted, cantilever parallelepipeds. The purpose of this… (more)

Subjects/Keywords: Airplanes – Wings, Swept-back.; Vibration (Aeronautics)

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APA (6^th Edition):

McGee, Oliver Gregory, I. (1988). A three dimensional elasticity based solution for free vibrations of simultaneously skewed and twisted cantilever parallelepipeds. (Doctoral Dissertation). University of Arizona. Retrieved from http://hdl.handle.net/10150/184517

Chicago Manual of Style (16^th Edition):

McGee, Oliver Gregory, III. “A three dimensional elasticity based solution for free vibrations of simultaneously skewed and twisted cantilever parallelepipeds. ” 1988. Doctoral Dissertation, University of Arizona. Accessed January 25, 2021. http://hdl.handle.net/10150/184517.

MLA Handbook (7^th Edition):

McGee, Oliver Gregory, III. “A three dimensional elasticity based solution for free vibrations of simultaneously skewed and twisted cantilever parallelepipeds. ” 1988. Web. 25 Jan 2021.

Vancouver:

McGee, Oliver Gregory I. A three dimensional elasticity based solution for free vibrations of simultaneously skewed and twisted cantilever parallelepipeds. [Internet] [Doctoral dissertation]. University of Arizona; 1988. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/10150/184517.

Council of Science Editors:

McGee, Oliver Gregory I. A three dimensional elasticity based solution for free vibrations of simultaneously skewed and twisted cantilever parallelepipeds. [Doctoral Dissertation]. University of Arizona; 1988. Available from: http://hdl.handle.net/10150/184517

27. Tufts, Matthew W. Computational Investigation of Sensitivity of the Crossflow Instability to Two-Dimensional Surface Imperfections.

Degree: PhD, Aerospace Engineering, 2015, Texas A&M University

URL: http://hdl.handle.net/1969.1/156386

► The interaction between two-dimensional steps and gaps with stationary crossﬂow vortices on a swept laminar wing has been investigated using computational methods. Using ﬂow conditions… (more)

Subjects/Keywords: Laminar Flow; Transition; Swept-Wing

…SWIFT Swept-Wing In-Flight Testing (Model with No Excrescence) SWIFTER Swept… …SWIFTEST Swept-Wing In-Flight Testing Excrescence Stability Theory (Model with 1% x/c… …Flows with Forward-Facing Steps . . . . . Unswept Open Flows with Swept Backward-Facing Steps… …Unswept Open Flows with Swept Forward-Facing Steps . Swept-Wing Flows with Backward-Facing Steps… …Swept-Wing Flows with Forward-Facing Steps . . . . . . Current Experiments…

11 more images…

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APA (6^th Edition):

Tufts, M. W. (2015). Computational Investigation of Sensitivity of the Crossflow Instability to Two-Dimensional Surface Imperfections. (Doctoral Dissertation). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/156386

Chicago Manual of Style (16^th Edition):

Tufts, Matthew W. “Computational Investigation of Sensitivity of the Crossflow Instability to Two-Dimensional Surface Imperfections.” 2015. Doctoral Dissertation, Texas A&M University. Accessed January 25, 2021. http://hdl.handle.net/1969.1/156386.

MLA Handbook (7^th Edition):

Tufts, Matthew W. “Computational Investigation of Sensitivity of the Crossflow Instability to Two-Dimensional Surface Imperfections.” 2015. Web. 25 Jan 2021.

Vancouver:

Tufts MW. Computational Investigation of Sensitivity of the Crossflow Instability to Two-Dimensional Surface Imperfections. [Internet] [Doctoral dissertation]. Texas A&M University; 2015. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1969.1/156386.

Council of Science Editors:

Tufts MW. Computational Investigation of Sensitivity of the Crossflow Instability to Two-Dimensional Surface Imperfections. [Doctoral Dissertation]. Texas A&M University; 2015. Available from: http://hdl.handle.net/1969.1/156386

28. Wiedemann, Arthur David. A Study of the Aeroacoustics of Swept Propellers for Small Unmanned Aerial Vehicles.

Degree: MS, Mechanical & Aerospace Engineering, 2020, Old Dominion University

URL: 9798641821429 ; https://digitalcommons.odu.edu/mae_etds/309

► In recent years, small unmanned aerial vehicles (UAVs) have increased in availability and use in both public and commercial sectors. This increased use of… (more)

Subjects/Keywords: Acoustics; Aeroacoustics; Aerodynamics; Propeller; Sweep; Swept; Acoustics, Dynamics, and Controls; Aerospace Engineering; Mechanical Engineering

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APA (6^th Edition):

Wiedemann, A. D. (2020). A Study of the Aeroacoustics of Swept Propellers for Small Unmanned Aerial Vehicles. (Thesis). Old Dominion University. Retrieved from 9798641821429 ; https://digitalcommons.odu.edu/mae_etds/309

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Wiedemann, Arthur David. “A Study of the Aeroacoustics of Swept Propellers for Small Unmanned Aerial Vehicles.” 2020. Thesis, Old Dominion University. Accessed January 25, 2021. 9798641821429 ; https://digitalcommons.odu.edu/mae_etds/309.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Wiedemann, Arthur David. “A Study of the Aeroacoustics of Swept Propellers for Small Unmanned Aerial Vehicles.” 2020. Web. 25 Jan 2021.

Vancouver:

Wiedemann AD. A Study of the Aeroacoustics of Swept Propellers for Small Unmanned Aerial Vehicles. [Internet] [Thesis]. Old Dominion University; 2020. [cited 2021 Jan 25]. Available from: 9798641821429 ; https://digitalcommons.odu.edu/mae_etds/309.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Wiedemann AD. A Study of the Aeroacoustics of Swept Propellers for Small Unmanned Aerial Vehicles. [Thesis]. Old Dominion University; 2020. Available from: 9798641821429 ; https://digitalcommons.odu.edu/mae_etds/309

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Delft University of Technology

29. Serpieri, J. Cross-Flow Instability: Flow diagnostics and control of swept wing boundary layers.

Degree: 2018, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:3dac1e78-fcc3-437f-9579-048b74439f55 ; urn:NBN:nl:ui:24-uuid:3dac1e78-fcc3-437f-9579-048b74439f55 ; 3dac1e78-fcc3-437f-9579-048b74439f55 ; 10.4233/uuid:3dac1e78-fcc3-437f-9579-048b74439f55 ; urn:isbn:978-94-6186-879-4 ; urn:NBN:nl:ui:24-uuid:3dac1e78-fcc3-437f-9579-048b74439f55 ; http://resolver.tudelft.nl/uuid:3dac1e78-fcc3-437f-9579-048b74439f55

► The research presented in this booklet focusses on the cross-flow instability. Applying traditional and advanced flow diagnostics, the boundary layer evolution is studied in detail.… (more)

Subjects/Keywords: Swept wings; Boundary layer transition; Cross-flow instability

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APA (6^th Edition):

Serpieri, J. (2018). Cross-Flow Instability: Flow diagnostics and control of swept wing boundary layers. (Doctoral Dissertation). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:3dac1e78-fcc3-437f-9579-048b74439f55 ; urn:NBN:nl:ui:24-uuid:3dac1e78-fcc3-437f-9579-048b74439f55 ; 3dac1e78-fcc3-437f-9579-048b74439f55 ; 10.4233/uuid:3dac1e78-fcc3-437f-9579-048b74439f55 ; urn:isbn:978-94-6186-879-4 ; urn:NBN:nl:ui:24-uuid:3dac1e78-fcc3-437f-9579-048b74439f55 ; http://resolver.tudelft.nl/uuid:3dac1e78-fcc3-437f-9579-048b74439f55

Chicago Manual of Style (16^th Edition):

Serpieri, J. “Cross-Flow Instability: Flow diagnostics and control of swept wing boundary layers.” 2018. Doctoral Dissertation, Delft University of Technology. Accessed January 25, 2021. http://resolver.tudelft.nl/uuid:3dac1e78-fcc3-437f-9579-048b74439f55 ; urn:NBN:nl:ui:24-uuid:3dac1e78-fcc3-437f-9579-048b74439f55 ; 3dac1e78-fcc3-437f-9579-048b74439f55 ; 10.4233/uuid:3dac1e78-fcc3-437f-9579-048b74439f55 ; urn:isbn:978-94-6186-879-4 ; urn:NBN:nl:ui:24-uuid:3dac1e78-fcc3-437f-9579-048b74439f55 ; http://resolver.tudelft.nl/uuid:3dac1e78-fcc3-437f-9579-048b74439f55.

MLA Handbook (7^th Edition):

Serpieri, J. “Cross-Flow Instability: Flow diagnostics and control of swept wing boundary layers.” 2018. Web. 25 Jan 2021.

Vancouver:

Serpieri J. Cross-Flow Instability: Flow diagnostics and control of swept wing boundary layers. [Internet] [Doctoral dissertation]. Delft University of Technology; 2018. [cited 2021 Jan 25]. Available from: http://resolver.tudelft.nl/uuid:3dac1e78-fcc3-437f-9579-048b74439f55 ; urn:NBN:nl:ui:24-uuid:3dac1e78-fcc3-437f-9579-048b74439f55 ; 3dac1e78-fcc3-437f-9579-048b74439f55 ; 10.4233/uuid:3dac1e78-fcc3-437f-9579-048b74439f55 ; urn:isbn:978-94-6186-879-4 ; urn:NBN:nl:ui:24-uuid:3dac1e78-fcc3-437f-9579-048b74439f55 ; http://resolver.tudelft.nl/uuid:3dac1e78-fcc3-437f-9579-048b74439f55.

Council of Science Editors:

Serpieri J. Cross-Flow Instability: Flow diagnostics and control of swept wing boundary layers. [Doctoral Dissertation]. Delft University of Technology; 2018. Available from: http://resolver.tudelft.nl/uuid:3dac1e78-fcc3-437f-9579-048b74439f55 ; urn:NBN:nl:ui:24-uuid:3dac1e78-fcc3-437f-9579-048b74439f55 ; 3dac1e78-fcc3-437f-9579-048b74439f55 ; 10.4233/uuid:3dac1e78-fcc3-437f-9579-048b74439f55 ; urn:isbn:978-94-6186-879-4 ; urn:NBN:nl:ui:24-uuid:3dac1e78-fcc3-437f-9579-048b74439f55 ; http://resolver.tudelft.nl/uuid:3dac1e78-fcc3-437f-9579-048b74439f55

University of Manchester

30. Chard, James. Tangential leading edge blowing for flow control on non-slender delta wings.

Degree: PhD, 2018, University of Manchester

URL: https://www.research.manchester.ac.uk/portal/en/theses/tangential-leading-edge-blowing-for-flow-control-on-nonslender-delta-wings(0ed0f6fa-23ad-44a2-a187-e8e1e8f1ac8a).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.748051

► In the military arena there is an increase in demand for Low Observable (LO) flight vehicles. This drive for low observability imposes limits on Leading… (more)

▼ In the military arena there is an increase in demand for Low Observable (LO) flight vehicles. This drive for low observability imposes limits on Leading Edge (LE) sweep angles and prohibits the use of a tailplane/fin resulting in unconventional configurations; a typical example of which are Unmanned Combat Aerial Vehicles (UCAVs). This class of aircraft poses stability and control problems due to the early onset of flow separation. The focus of this project is on the on the use of Tangential Leading Edge Blowing (TLEB) as a means of separation suppression on such vehicles. This project is unique in that the TLEB slot is positioned on the wing lower surface facing the oncoming freestream. Also, the model in this project is representative of the outboard panel of a UCAV wing, a geometry on which TLEB has not been explored in the past. A swept wing model (LE sweep = 47 degrees, AR = 3) was designed. The model has a TLEB nozzle with a slot on the lower surface at approx. 1% yawed chord that spans 0.58 m (approx. 70% LE length). Baseline wing characteristics were obtained with the full slot exposed. The wing showed a variation in pitch between CL = 0 and 0.6 which from oil flow visualisation is believed to be due to laminar separation. At CL = 0.6 there is a positive pitch break which flow visualisation suggests is due to the occurrence of a LE vortex. Sensitivity studies for slot configuration, Re number and transition fixing were carried out. The blowing rates 0.0025, 0.005, 0.025, 0.05 were tested for two slot lengths; one full span (0.58 m) and another third span positioned at the midpoint of the full slot. All blowing rates show some suppression of the LE vortex and therefore reduction in severity of the pitch break at CL = 0.6. High blowing rates produce a negative shift in CM, which CFD suggests is due to a large amount of suction produced on the lower wing surface adjacent to the slot exit. This means the available trim power is less than for the lower blowing rates. Wool tuft results for high blowing rates from the middle slot show an increase in streamwise flow at the TE suggesting TLEB is capable of improving the effectiveness of TE devices. The effectiveness of TLEB at low blowing rates has been shown to be high compared to that found in literature. A 1st order analysis of the impact of TLEB on a full scale system shows realistic options.

Subjects/Keywords: 629.13; Leading edge separation; Delta wing; UCAV; Tangential blowing; Swept wing; Flow control; Leading edge blowing; Fluidic control

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APA (6^th Edition):

Chard, J. (2018). Tangential leading edge blowing for flow control on non-slender delta wings. (Doctoral Dissertation). University of Manchester. Retrieved from https://www.research.manchester.ac.uk/portal/en/theses/tangential-leading-edge-blowing-for-flow-control-on-nonslender-delta-wings(0ed0f6fa-23ad-44a2-a187-e8e1e8f1ac8a).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.748051

Chicago Manual of Style (16^th Edition):

Chard, James. “Tangential leading edge blowing for flow control on non-slender delta wings.” 2018. Doctoral Dissertation, University of Manchester. Accessed January 25, 2021. https://www.research.manchester.ac.uk/portal/en/theses/tangential-leading-edge-blowing-for-flow-control-on-nonslender-delta-wings(0ed0f6fa-23ad-44a2-a187-e8e1e8f1ac8a).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.748051.

MLA Handbook (7^th Edition):

Chard, James. “Tangential leading edge blowing for flow control on non-slender delta wings.” 2018. Web. 25 Jan 2021.

Vancouver:

Chard J. Tangential leading edge blowing for flow control on non-slender delta wings. [Internet] [Doctoral dissertation]. University of Manchester; 2018. [cited 2021 Jan 25]. Available from: https://www.research.manchester.ac.uk/portal/en/theses/tangential-leading-edge-blowing-for-flow-control-on-nonslender-delta-wings(0ed0f6fa-23ad-44a2-a187-e8e1e8f1ac8a).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.748051.

Council of Science Editors:

Chard J. Tangential leading edge blowing for flow control on non-slender delta wings. [Doctoral Dissertation]. University of Manchester; 2018. Available from: https://www.research.manchester.ac.uk/portal/en/theses/tangential-leading-edge-blowing-for-flow-control-on-nonslender-delta-wings(0ed0f6fa-23ad-44a2-a187-e8e1e8f1ac8a).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.748051

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