subject:( Swept gull wing configuration)

University of Pretoria

1. [No author]. Longitudinal handling characteristics of a tailless gull-wing aircraft .

Degree: 2008, University of Pretoria

URL: http://upetd.up.ac.za/thesis/available/etd-09182008-132941/

► A handling quality investigation was performed on the swept gull-wing configuration. The swept gull-wing configuration is tailless and has a wing with a transition in… (more)

Subjects/Keywords: Flight simulation; Tumbling; Thumbprint criterion; Neal-smith analysis; C-star criterion; Shomber-gertsen analysis; Pilot induced oscillation; Oswald efficiency; Pilot mathematical model; Variable sweep wing; Exulans; Variable static margin; Swept gull-wing configuration; O-point; E-point; Handling qualities; Gust handling qualities; Tailless aircraft; Pecking; Monnich and dalldorff criterion; UCTD

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APA (6^th Edition):

author], [. (2008). Longitudinal handling characteristics of a tailless gull-wing aircraft . (Masters Thesis). University of Pretoria. Retrieved from http://upetd.up.ac.za/thesis/available/etd-09182008-132941/

Chicago Manual of Style (16^th Edition):

author], [No. “Longitudinal handling characteristics of a tailless gull-wing aircraft .” 2008. Masters Thesis, University of Pretoria. Accessed January 24, 2021. http://upetd.up.ac.za/thesis/available/etd-09182008-132941/.

MLA Handbook (7^th Edition):

author], [No. “Longitudinal handling characteristics of a tailless gull-wing aircraft .” 2008. Web. 24 Jan 2021.

Vancouver:

author] [. Longitudinal handling characteristics of a tailless gull-wing aircraft . [Internet] [Masters thesis]. University of Pretoria; 2008. [cited 2021 Jan 24]. Available from: http://upetd.up.ac.za/thesis/available/etd-09182008-132941/.

Council of Science Editors:

author] [. Longitudinal handling characteristics of a tailless gull-wing aircraft . [Masters Thesis]. University of Pretoria; 2008. Available from: http://upetd.up.ac.za/thesis/available/etd-09182008-132941/

University of Pretoria

2. Agenbag, Daniel Sarel. Longitudinal handling characteristics of a tailless gull-wing aircraft.

Degree: Mechanical and Aeronautical Engineering, 2008, University of Pretoria

URL: http://hdl.handle.net/2263/28011

► A handling quality investigation was performed on the swept gull-wing configuration. The swept gull-wing configuration is tailless and has a wing with a transition in… (more)

Subjects/Keywords: Flight simulation; Tumbling; Thumbprint criterion; Neal-smith analysis; C-star criterion; Shomber-gertsen analysis; Pilot induced oscillation; Oswald efficiency; Pilot mathematical model; Variable sweep wing; Exulans; Variable static margin; Swept gull-wing configuration; O-point; E-point; Handling qualities; Gust handling qualities; Tailless aircraft; Pecking; Monnich and dalldorff criterion; UCTD

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

APA (6^th Edition):

Agenbag, D. (2008). Longitudinal handling characteristics of a tailless gull-wing aircraft. (Masters Thesis). University of Pretoria. Retrieved from http://hdl.handle.net/2263/28011

Chicago Manual of Style (16^th Edition):

Agenbag, Daniel. “Longitudinal handling characteristics of a tailless gull-wing aircraft.” 2008. Masters Thesis, University of Pretoria. Accessed January 24, 2021. http://hdl.handle.net/2263/28011.

MLA Handbook (7^th Edition):

Agenbag, Daniel. “Longitudinal handling characteristics of a tailless gull-wing aircraft.” 2008. Web. 24 Jan 2021.

Vancouver:

Agenbag D. Longitudinal handling characteristics of a tailless gull-wing aircraft. [Internet] [Masters thesis]. University of Pretoria; 2008. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/2263/28011.

Council of Science Editors:

Agenbag D. Longitudinal handling characteristics of a tailless gull-wing aircraft. [Masters Thesis]. University of Pretoria; 2008. Available from: http://hdl.handle.net/2263/28011

Delft University of Technology

3. 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 (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 24, 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. 24 Jan 2021.

Vancouver:

Sol MB(. Conceptual Design of Swept Wing Root Aerofoils. [Internet] [Masters thesis]. Delft University of Technology; 2015. [cited 2021 Jan 24]. 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

4. 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 24, 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. 24 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 24]. 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 Arizona

5. 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 (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 24, 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. 24 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 24]. 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

6. 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 24, 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. 24 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 24]. 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

Lehigh University

7. 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 24, 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. 24 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 24]. 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

Cranfield University

8. Huang, Haidong. Optimal design of a flying-wing aircraft inner wing structure configuration.

Degree: MSc by Research, 2012, Cranfield University

URL: http://dspace.lib.cranfield.ac.uk/handle/1826/7439

► Flying-wing aircraft are considered to have great advantages and potentials in aerodynamic performance and weight saving. However, they also have many challenges in design. One… (more)

▼ Flying-wing aircraft are considered to have great advantages and potentials in aerodynamic performance and weight saving. However, they also have many challenges in design. One of the biggest challenges is the structural design of the inner wing (fuselage). Unlike the conventional fuselage of a tube configuration, the flying-wing aircraft inner wing cross section is limited to a noncircular shape, which is not structurally efficient to resist the internal pressure load. In order to solve this problem, a number of configurations have been proposed by other designers such as Multi Bubble Fuselage (MBF), Vaulted Ribbed Shell (VLRS), Flat Ribbed Shell (FRS), Vaulted Shell Honeycomb Core (VLHC), Flat Sandwich Shell Honeycomb Core (FLHC), Y Braced Box Fuselage and the modified fuselage designed with Y brace replaced by vaulted shell configurations. However all these configurations still inevitably have structural weight penalty compared with optimal tube fuselage layout. This current study intends to focus on finding an optimal configuration with minimum structural weight penalty for a flying-wing concept in a preliminary design stage. A new possible inner wing configuration, in terms of aerodynamic shape and structural layout, was proposed by the author, and it might be referred as ‘Wave-Section Configuration’. The methodologies of how to obtain a structurally efficient curvature of the shape, as well as how to conduct the initial sizing were incorporated. A theoretical analysis of load transmission indicated that the Wave-Section Configuration is feasible, and this was further proved as being practical by FE analysis. Moreover, initial FE analysis and comparison of the Wave-Section Configuration with two other typical configurations, Multi Bubble Fuselage and Conventional Wing, suggested that the Wave-Section Configuration is an optimal design in terms of weight saving. However, due to limitations of the author’s research area, influences on aerodynamic performances have not yet been taken into account.

Subjects/Keywords: Flying-wing aircraft; inner wing configuration; Wave-Section Configuration; optimal; FE analysis

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APA (6^th Edition):

Huang, H. (2012). Optimal design of a flying-wing aircraft inner wing structure configuration. (Masters Thesis). Cranfield University. Retrieved from http://dspace.lib.cranfield.ac.uk/handle/1826/7439

Chicago Manual of Style (16^th Edition):

Huang, Haidong. “Optimal design of a flying-wing aircraft inner wing structure configuration.” 2012. Masters Thesis, Cranfield University. Accessed January 24, 2021. http://dspace.lib.cranfield.ac.uk/handle/1826/7439.

MLA Handbook (7^th Edition):

Huang, Haidong. “Optimal design of a flying-wing aircraft inner wing structure configuration.” 2012. Web. 24 Jan 2021.

Vancouver:

Huang H. Optimal design of a flying-wing aircraft inner wing structure configuration. [Internet] [Masters thesis]. Cranfield University; 2012. [cited 2021 Jan 24]. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/7439.

Council of Science Editors:

Huang H. Optimal design of a flying-wing aircraft inner wing structure configuration. [Masters Thesis]. Cranfield University; 2012. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/7439

9. Barbosa, Átila Antunes França. Influência da asa em gaivota nos coeficientes aerodinâmicos de uma aeronave.

Degree: Mestrado, Aeronaves, 2015, University of São Paulo

URL: http://www.teses.usp.br/teses/disponiveis/18/18148/tde-15112015-170422/ ;

►

Desde o início da década de 2010, o aumento do preço do combustível de aviação e a pressão da sociedade para redução da emissão de… (more)

▼

Desde o início da década de 2010, o aumento do preço do combustível de aviação e a pressão da sociedade para redução da emissão de gases nocivos ao meio ambiente, junto com a necessidade de redução de ruído durante as fases de decolagem e pouso, levaram as companhias aéreas a buscar aeronaves mais eficientes. Para suprir essa demanda, os fabricantes de aviões comerciais solucionaram esse problema através do uso de motores de maior desempenho, que apresentam maior diâmetro que motores de gerações passadas. Desse modo, foi necessário projetar asas com maior diedro na região da raiz, possibilitando a instalação desses novos motores, e diedro menor após a seção do motor, adotando assim a solução de asa em gaivota. O presente trabalho visa analisar o impacto de diferentes tipos de asas em gaivota nos coeficientes aerodinâmicos de uma aeronave de configuração comercial típica. Para tanto, foi realizada uma revisão bibliográfica dos estudos envolvendo asas em gaivota. Numa primeira fase foi feito um estudo analítico das características aerodinâmicas de alguns modelos de aeronaves com asa em gaivota, e em uma segunda fase, foram empregadas ferramentas computacionais para analisar seus comportamentos aerodinâmicos. Posteriormente, em uma terceira fase, esses modelos foram ensaiados no túnel de vento do LAE (Laboratório de Aerodinâmica da EESC/USP), e os resultados das três fases foram comparados.

Since the beginning of the 2010s, the increasing price of aviation fuel and the pressure of society to reduce the emission of harmful gases into the environment, coupled with the need of noise reduction during the takeoff and landing, induce carrier companies to look for more efficient airplanes. To furnish this demand, the airplane manufacturers solved the problem using high performance engines, which present a larger diameter than the engines from previous generations. Thereby, it was necessary to project wing with higher dihedral on the root portion, enabling the installation of these new engines, and a lower dihedral after the engine section, thus adopting a gull wing solution. This research project aims at analyzing the impact of different types of gull wing on the aerodynamic coefficients of a typical commercial configuration airplane. For this purpose, a bibliographic review about the studies related to gull wings was performed. In a first phase, an analytical analysis of the aerodynamic characteristics of some airplane model with gull wings was done, and in a second phase, computational programs was used to study their aerodynamic behavior. Later, in a third phase, these models were tested in the wind tunnel of LAE (Laboratory of Aerodynamics of EESC/USP), and the results from the three phases were compared.

Advisors/Committee Members: Catalano, Fernando Martini.

Subjects/Keywords: Asas com diedro variável; Asas em gaivota; Ensaio em túnel de vento; Gull wing; Multi dihedral wing; Wind tunnel testing

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APA (6^th Edition):

Barbosa, �. A. F. (2015). Influência da asa em gaivota nos coeficientes aerodinâmicos de uma aeronave. (Masters Thesis). University of São Paulo. Retrieved from http://www.teses.usp.br/teses/disponiveis/18/18148/tde-15112015-170422/ ;

Chicago Manual of Style (16^th Edition):

Barbosa, Átila Antunes França. “Influência da asa em gaivota nos coeficientes aerodinâmicos de uma aeronave.” 2015. Masters Thesis, University of São Paulo. Accessed January 24, 2021. http://www.teses.usp.br/teses/disponiveis/18/18148/tde-15112015-170422/ ;.

MLA Handbook (7^th Edition):

Barbosa, Átila Antunes França. “Influência da asa em gaivota nos coeficientes aerodinâmicos de uma aeronave.” 2015. Web. 24 Jan 2021.

Vancouver:

Barbosa �AF. Influência da asa em gaivota nos coeficientes aerodinâmicos de uma aeronave. [Internet] [Masters thesis]. University of São Paulo; 2015. [cited 2021 Jan 24]. Available from: http://www.teses.usp.br/teses/disponiveis/18/18148/tde-15112015-170422/ ;.

Council of Science Editors:

Barbosa �AF. Influência da asa em gaivota nos coeficientes aerodinâmicos de uma aeronave. [Masters Thesis]. University of São Paulo; 2015. Available from: http://www.teses.usp.br/teses/disponiveis/18/18148/tde-15112015-170422/ ;

10. 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…

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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 24, 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. 24 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 24]. 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

University of Washington

11. 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 24, 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. 24 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 24]. 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

12. 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 24, 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. 24 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 24]. 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

13. 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… …Unswept Open Flows with Swept Forward-Facing Steps . Swept-Wing Flows with Backward-Facing Steps… …Swept-Wing Flows with Forward-Facing Steps . . . . . . Current Experiments… …TRAVELING MODES . . . . . . . 120 xi LIST OF FIGURES FIGURE Page I.1 Swept-Wing Velocity…

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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 24, 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. 24 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 24]. 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

University of Manchester

14. 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 24, 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. 24 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 24]. 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

Virginia Tech

15. Orr, Matthew William. Aerodynamic Properties of the Inboard Wing Concept.

Degree: MS, Aerospace Engineering, 2003, Virginia Tech

URL: http://hdl.handle.net/10919/9708

► This investigation examines a new concept in airliner configurations from an experimental aerodynamics point of view. The concept proposes mounting the fuselages at the tips… (more)

Subjects/Keywords: configuration testing; aerodynamics; inboard wing

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APA (6^th Edition):

Orr, M. W. (2003). Aerodynamic Properties of the Inboard Wing Concept. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/9708

Chicago Manual of Style (16^th Edition):

Orr, Matthew William. “Aerodynamic Properties of the Inboard Wing Concept.” 2003. Masters Thesis, Virginia Tech. Accessed January 24, 2021. http://hdl.handle.net/10919/9708.

MLA Handbook (7^th Edition):

Orr, Matthew William. “Aerodynamic Properties of the Inboard Wing Concept.” 2003. Web. 24 Jan 2021.

Vancouver:

Orr MW. Aerodynamic Properties of the Inboard Wing Concept. [Internet] [Masters thesis]. Virginia Tech; 2003. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/10919/9708.

Council of Science Editors:

Orr MW. Aerodynamic Properties of the Inboard Wing Concept. [Masters Thesis]. Virginia Tech; 2003. Available from: http://hdl.handle.net/10919/9708

Delft University of Technology

16. Boersma, J.Y. (author). Business Jet Design Using Laminar Flow.

Degree: 2016, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:4d1818ec-5842-47b0-b144-173aa77a3803

►

For conceptual aircraft design to include accurate laminar flow prediction, a link between modern computational tools to determine laminar-to-turbulent boundary layer transition and fast sizing… (more)

Subjects/Keywords: drag; N-factor; boundary layer; skin friction; laminar; flow; transition; Reynolds; crossflow; aircraft; design; business; swept; wing; initiator; model

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APA (6^th Edition):

Boersma, J. Y. (. (2016). Business Jet Design Using Laminar Flow. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:4d1818ec-5842-47b0-b144-173aa77a3803

Chicago Manual of Style (16^th Edition):

Boersma, J Y (author). “Business Jet Design Using Laminar Flow.” 2016. Masters Thesis, Delft University of Technology. Accessed January 24, 2021. http://resolver.tudelft.nl/uuid:4d1818ec-5842-47b0-b144-173aa77a3803.

MLA Handbook (7^th Edition):

Boersma, J Y (author). “Business Jet Design Using Laminar Flow.” 2016. Web. 24 Jan 2021.

Vancouver:

Boersma JY(. Business Jet Design Using Laminar Flow. [Internet] [Masters thesis]. Delft University of Technology; 2016. [cited 2021 Jan 24]. Available from: http://resolver.tudelft.nl/uuid:4d1818ec-5842-47b0-b144-173aa77a3803.

Council of Science Editors:

Boersma JY(. Business Jet Design Using Laminar Flow. [Masters Thesis]. Delft University of Technology; 2016. Available from: http://resolver.tudelft.nl/uuid:4d1818ec-5842-47b0-b144-173aa77a3803

Texas A&M University

17. Belisle, Michael Joseph. Aerodynamic Design for Swept-wing Laminar Flow.

Degree: PhD, Aerospace Engineering, 2013, Texas A&M University

URL: http://hdl.handle.net/1969.1/151655

► This work describes and compares processes for swept-wing laminar flow control (SWLFC) aerody-namic design. It focuses on results obtained during the preliminary outer-mold-line (OML) design… (more)

▼ This work describes and compares processes for swept-wing laminar flow control (SWLFC) aerody-namic design. It focuses on results obtained during the preliminary outer-mold-line (OML) design of the Subsonic Aircraft Roughness Glove Experiment (SARGE), a natural laminar flow and passive laminar flow control wing glove flight experiment funded by the NASA Environmentally Responsible Aviation initiative. The experiment seeks to raise the technology readiness level of the spanwise-periodic discrete roughness element (DRE) SWLFC technique for transition delay on a swept wing. Changes to the SARGE project requirements necessitated numerous redesigns that lead to design process insights and reinforced the value of proven methodologies. Optimization-based wing design methods are compared to traditional processes in the context of issues specific to SWLFC design. A refined traditional process incorporates the lessons learned during SARGE design excursions. As 3D eﬀects are often significant at transonic Mach numbers, they should be included in the analysis as soon as practical when allowing for available computational tools. In the initial experimental feasibility and OML design, Euler computational fluid dynamics was used to produce a series of 2.5D SWLFC airfoils with boundary-layer stability and transition predicted using linear stability theory and the e^(N) method. Two wing gloves were lofted onto the Gulfstream-III host aircraft wing: TAMU-05-04, a straight loft using the TAMU2D-04 airfoils, and TAMU-06-05, an optimized revision used in the preliminary design review (PDR) of the SARGE experiment conducted in June 2012. The target pressure distribution for the TAMU-06-05 glove was developed using a graphical B-spline method. The SARGE PDR identified a few issues that need to be addressed in order to ensure a successful experiment, which includes isobar unsweep that adversely aﬀects boundary layer stability for DRE control and potential flow separation at the inboard fairing. Using the refined process, an alternate planform is evaluated as a potential starting point to address these issues and is shown to be feasible. Advisors/Committee Members: Saric, William S (advisor), Reed, Helen L (committee member), White, Edward B (committee member), Bowersox, Rodney D (committee member), Ranjan, Devesh (committee member).

Subjects/Keywords: aircraft; aerodynamic design; boundary-layer stability; boundary-layer transition; crossflow instability; discrete roughness elements; drag reduction; flight test; laminar flow control; natural laminar flow; swept-wing laminar flow control; wing design; wing glove

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

APA (6^th Edition):

Belisle, M. J. (2013). Aerodynamic Design for Swept-wing Laminar Flow. (Doctoral Dissertation). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/151655

Chicago Manual of Style (16^th Edition):

Belisle, Michael Joseph. “Aerodynamic Design for Swept-wing Laminar Flow.” 2013. Doctoral Dissertation, Texas A&M University. Accessed January 24, 2021. http://hdl.handle.net/1969.1/151655.

MLA Handbook (7^th Edition):

Belisle, Michael Joseph. “Aerodynamic Design for Swept-wing Laminar Flow.” 2013. Web. 24 Jan 2021.

Vancouver:

Belisle MJ. Aerodynamic Design for Swept-wing Laminar Flow. [Internet] [Doctoral dissertation]. Texas A&M University; 2013. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/1969.1/151655.

Council of Science Editors:

Belisle MJ. Aerodynamic Design for Swept-wing Laminar Flow. [Doctoral Dissertation]. Texas A&M University; 2013. Available from: http://hdl.handle.net/1969.1/151655

Brno University of Technology

18. Musil, Tomáš. Netradiční koncepce letadel: Non-Traditional Aircraft Conception.

Degree: 2018, Brno University of Technology

URL: http://hdl.handle.net/11012/81578

► This bachelor thesis is about concepts of aircraft that are non-traditional in structural design or unconventional in different aspects. The individual chapters describe selected concepts… (more)

Subjects/Keywords: Koncepce letadla; nekonvenční letoun; VTOL; negativní geometrie křídla; samokřídlo; tailsitter; konvertoplán; vektorování tahu; šikmé křídlo; vztlakové těleso; Aircraft conception; unconventional aircraft; VTOL; forward-swept wing; flying wing; tailsitter; convertiplane; thrust vectoring; oblique wing; lifting body

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APA (6^th Edition):

Musil, T. (2018). Netradiční koncepce letadel: Non-Traditional Aircraft Conception. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/81578

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):

Musil, Tomáš. “Netradiční koncepce letadel: Non-Traditional Aircraft Conception.” 2018. Thesis, Brno University of Technology. Accessed January 24, 2021. http://hdl.handle.net/11012/81578.

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

MLA Handbook (7^th Edition):

Musil, Tomáš. “Netradiční koncepce letadel: Non-Traditional Aircraft Conception.” 2018. Web. 24 Jan 2021.

Vancouver:

Musil T. Netradiční koncepce letadel: Non-Traditional Aircraft Conception. [Internet] [Thesis]. Brno University of Technology; 2018. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/11012/81578.

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

Council of Science Editors:

Musil T. Netradiční koncepce letadel: Non-Traditional Aircraft Conception. [Thesis]. Brno University of Technology; 2018. Available from: http://hdl.handle.net/11012/81578

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

University of Florida

19. Lacroix, Bradley W. On the Mechanics, Computational Modeling, and Design Implementation of Piezoelectric Actuators on Micro Air Vehicles.

Degree: PhD, Mechanical Engineering - Mechanical and Aerospace Engineering, 2013, University of Florida

URL: https://ufdc.ufl.edu/UFE0046212

► This document details the research performed on applying piezoelectric macro fiber composite actuators on micro air vehicles. The research objective was to apply the minimum… (more)

Subjects/Keywords: Aircraft; Aircraft pitch; Aircraft roll; Aircraft wings; Carbon fibers; Design optimization; Geometry; Steels; Swept wings; Wind tunnels; composite – fiber – flying – macro – materials – mav – mfc – morphing – optimization – piezoelectric – smart – uav – wing

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APA (6^th Edition):

Lacroix, B. W. (2013). On the Mechanics, Computational Modeling, and Design Implementation of Piezoelectric Actuators on Micro Air Vehicles. (Doctoral Dissertation). University of Florida. Retrieved from https://ufdc.ufl.edu/UFE0046212

Chicago Manual of Style (16^th Edition):

Lacroix, Bradley W. “On the Mechanics, Computational Modeling, and Design Implementation of Piezoelectric Actuators on Micro Air Vehicles.” 2013. Doctoral Dissertation, University of Florida. Accessed January 24, 2021. https://ufdc.ufl.edu/UFE0046212.

MLA Handbook (7^th Edition):

Lacroix, Bradley W. “On the Mechanics, Computational Modeling, and Design Implementation of Piezoelectric Actuators on Micro Air Vehicles.” 2013. Web. 24 Jan 2021.

Vancouver:

Lacroix BW. On the Mechanics, Computational Modeling, and Design Implementation of Piezoelectric Actuators on Micro Air Vehicles. [Internet] [Doctoral dissertation]. University of Florida; 2013. [cited 2021 Jan 24]. Available from: https://ufdc.ufl.edu/UFE0046212.

Council of Science Editors:

Lacroix BW. On the Mechanics, Computational Modeling, and Design Implementation of Piezoelectric Actuators on Micro Air Vehicles. [Doctoral Dissertation]. University of Florida; 2013. Available from: https://ufdc.ufl.edu/UFE0046212

20. Weissenfluh, Shawn Edward. Quantifying Seasonal Variation in Physiological Condition of Adult Franklin's Gull (Luecophaeus Pipixcan) during Nesting.

Degree: 2011, North Dakota State University

URL: http://hdl.handle.net/10365/28844

► Understanding seasonal variation in adult physiological condition is important for developing hypotheses on how nest initiation, adult condition, chick development and recruitment are related in… (more)

Subjects/Keywords: Franklin's gull – Physiology.; Franklin's gull – Reproduction.; Franklin's gull – Nests.

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APA (6^th Edition):

Weissenfluh, S. E. (2011). Quantifying Seasonal Variation in Physiological Condition of Adult Franklin's Gull (Luecophaeus Pipixcan) during Nesting. (Thesis). North Dakota State University. Retrieved from http://hdl.handle.net/10365/28844

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):

Weissenfluh, Shawn Edward. “Quantifying Seasonal Variation in Physiological Condition of Adult Franklin's Gull (Luecophaeus Pipixcan) during Nesting.” 2011. Thesis, North Dakota State University. Accessed January 24, 2021. http://hdl.handle.net/10365/28844.

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

MLA Handbook (7^th Edition):

Weissenfluh, Shawn Edward. “Quantifying Seasonal Variation in Physiological Condition of Adult Franklin's Gull (Luecophaeus Pipixcan) during Nesting.” 2011. Web. 24 Jan 2021.

Vancouver:

Weissenfluh SE. Quantifying Seasonal Variation in Physiological Condition of Adult Franklin's Gull (Luecophaeus Pipixcan) during Nesting. [Internet] [Thesis]. North Dakota State University; 2011. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/10365/28844.

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

Council of Science Editors:

Weissenfluh SE. Quantifying Seasonal Variation in Physiological Condition of Adult Franklin's Gull (Luecophaeus Pipixcan) during Nesting. [Thesis]. North Dakota State University; 2011. Available from: http://hdl.handle.net/10365/28844

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

Indian Institute of Science

21. Nathan, Vinay. Analysis of Unsteady Incompressible Potential Flow Over a Swimming Slender Fish and a Swept Wing Tail.

Degree: MSc Engg, Faculty of Engineering, 2018, Indian Institute of Science

URL: http://etd.iisc.ac.in/handle/2005/3551

► This thesis deals with computing the pressure distribution around a swimming slender fish and the thrust generated by its flapping motion. The body of the… (more)

Subjects/Keywords: Swimming Slender Fish Flow Dynamics; Slender Body Flow Model; Swept Wing Model; Planar Wing Flow; Unsteady Flows; Vortex Dynamics; Swimming Propulsion; Unsteady Propulsion; Fishlike Swimmimg Hydrodynamics; Fish Near-Body Flow Dynamics; Marine Propulsion; Fluid Dynamics; Vortex Panel Method; Bernoulli Equation; Aerospace Engineering

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APA (6^th Edition):

Nathan, V. (2018). Analysis of Unsteady Incompressible Potential Flow Over a Swimming Slender Fish and a Swept Wing Tail. (Masters Thesis). Indian Institute of Science. Retrieved from http://etd.iisc.ac.in/handle/2005/3551

Chicago Manual of Style (16^th Edition):

Nathan, Vinay. “Analysis of Unsteady Incompressible Potential Flow Over a Swimming Slender Fish and a Swept Wing Tail.” 2018. Masters Thesis, Indian Institute of Science. Accessed January 24, 2021. http://etd.iisc.ac.in/handle/2005/3551.

MLA Handbook (7^th Edition):

Nathan, Vinay. “Analysis of Unsteady Incompressible Potential Flow Over a Swimming Slender Fish and a Swept Wing Tail.” 2018. Web. 24 Jan 2021.

Vancouver:

Nathan V. Analysis of Unsteady Incompressible Potential Flow Over a Swimming Slender Fish and a Swept Wing Tail. [Internet] [Masters thesis]. Indian Institute of Science; 2018. [cited 2021 Jan 24]. Available from: http://etd.iisc.ac.in/handle/2005/3551.

Council of Science Editors:

Nathan V. Analysis of Unsteady Incompressible Potential Flow Over a Swimming Slender Fish and a Swept Wing Tail. [Masters Thesis]. Indian Institute of Science; 2018. Available from: http://etd.iisc.ac.in/handle/2005/3551

22. Adegbindin, Moustaine Kolawole Agnide. Control Power Optimization using Artificial Intelligence for Forward Swept Wing and Hybrid Wing Body Aircraft.

Degree: MS, Aerospace Engineering, 2017, Virginia Tech

URL: http://hdl.handle.net/10919/74950

► Many futuristic aircraft such as the Hybrid Wing Body have numerous control surfaces that can result in large hinge moments, high actuation power demands, and… (more)

Subjects/Keywords: Optimization; Artificial Intelligence; Neural Network; Genetic Algorithm; Forward Swept Wing; Hybrid Wing Body; Hinge Moment

…Forward Swept Wing GA : Genetic Algorithm HM : Hinge Moments xiv HWB : Hybrid Wing… …Forward Swept Wing (FSW) aircraft. 4 2 Aircraft Configurations Studied 2.1 Hybrid… …Wing Body (HWB) A Hybrid Wing Body aircraft is a configuration where the wing and… …Swept Wing (FSW) A Forward Swept Wing (FSW) aircraft was selected as a… …Laboratory have developed a Hybrid Wing Body aircraft concept: the X48 (see Fig. 1.1)…

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APA (6^th Edition):

Adegbindin, M. K. A. (2017). Control Power Optimization using Artificial Intelligence for Forward Swept Wing and Hybrid Wing Body Aircraft. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/74950

Chicago Manual of Style (16^th Edition):

Adegbindin, Moustaine Kolawole Agnide. “Control Power Optimization using Artificial Intelligence for Forward Swept Wing and Hybrid Wing Body Aircraft.” 2017. Masters Thesis, Virginia Tech. Accessed January 24, 2021. http://hdl.handle.net/10919/74950.

MLA Handbook (7^th Edition):

Adegbindin, Moustaine Kolawole Agnide. “Control Power Optimization using Artificial Intelligence for Forward Swept Wing and Hybrid Wing Body Aircraft.” 2017. Web. 24 Jan 2021.

Vancouver:

Adegbindin MKA. Control Power Optimization using Artificial Intelligence for Forward Swept Wing and Hybrid Wing Body Aircraft. [Internet] [Masters thesis]. Virginia Tech; 2017. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/10919/74950.

Council of Science Editors:

Adegbindin MKA. Control Power Optimization using Artificial Intelligence for Forward Swept Wing and Hybrid Wing Body Aircraft. [Masters Thesis]. Virginia Tech; 2017. Available from: http://hdl.handle.net/10919/74950

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

Degree: 2018, University of Manchester

URL: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:314613

► 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. Advisors/Committee Members: SMITH, KATHARINE KL, Crowther, William, Smith, Katharine.

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

…x28;61)....... 91 Figure 53: TLEB configuration on the Buccaneer Mark 1 swept wing (… …Figure 12: Leading edge separation bubble on a moderately swept wing (flow in direction of… …50 Figure 13: Upper surface attached pressure distribution on a swept wing. Taken from… …swept wing. Taken from (30)… …52 Figure 16: Leading edge vortex flow on a moderately swept wing (flow in direction…

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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 http://www.manchester.ac.uk/escholar/uk-ac-man-scw:314613

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 24, 2021. http://www.manchester.ac.uk/escholar/uk-ac-man-scw:314613.

MLA Handbook (7^th Edition):

Chard, James. “Tangential leading edge blowing for flow control on non-slender delta wings.” 2018. Web. 24 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 24]. Available from: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:314613.

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: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:314613

Michigan State University

24. Smith, William John. Movements of Michigan herring gulls.

Degree: MS, 1958, Michigan State University

URL: http://etd.lib.msu.edu/islandora/object/etd:13101

Subjects/Keywords: Herring gull

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APA (6^th Edition):

Smith, W. J. (1958). Movements of Michigan herring gulls. (Masters Thesis). Michigan State University. Retrieved from http://etd.lib.msu.edu/islandora/object/etd:13101

Chicago Manual of Style (16^th Edition):

Smith, William John. “Movements of Michigan herring gulls.” 1958. Masters Thesis, Michigan State University. Accessed January 24, 2021. http://etd.lib.msu.edu/islandora/object/etd:13101.

MLA Handbook (7^th Edition):

Smith, William John. “Movements of Michigan herring gulls.” 1958. Web. 24 Jan 2021.

Vancouver:

Smith WJ. Movements of Michigan herring gulls. [Internet] [Masters thesis]. Michigan State University; 1958. [cited 2021 Jan 24]. Available from: http://etd.lib.msu.edu/islandora/object/etd:13101.

Council of Science Editors:

Smith WJ. Movements of Michigan herring gulls. [Masters Thesis]. Michigan State University; 1958. Available from: http://etd.lib.msu.edu/islandora/object/etd:13101

25. Woodruff, Matthew Jeffery. Receptivity Studies on a Swept-Wing Model.

Degree: MS, Aerospace Engineering, 2012, Texas A&M University

URL: http://hdl.handle.net/1969.1/ETD-TAMU-2011-05-9119

► A series of flight tests was performed using a swept-wing model mounted on a Cessna O-2 aircraft. The crossflow waves on the airfoil were excited… (more)

Subjects/Keywords: laminar flow control; laminar to turbulent transition; swept wing flow control

…the last major hurdle in swept-wing laminar flow control (SWLFC) (Saric… …work relevant to the current experiment. The Swept-Wing In Flight Testing (SWIFT)… …The Swept-Wing In Flight Testing (SWIFT) model is an airfoil that has been… …with the flight crew during flight operations. TEST AIRFOIL The Swept Wing In Flight Testing… …x28;SWIFT) model used for these series of tests is a 30° swept wing with a laminar flow…

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APA (6^th Edition):

Woodruff, M. J. (2012). Receptivity Studies on a Swept-Wing Model. (Masters Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/ETD-TAMU-2011-05-9119

Chicago Manual of Style (16^th Edition):

Woodruff, Matthew Jeffery. “Receptivity Studies on a Swept-Wing Model.” 2012. Masters Thesis, Texas A&M University. Accessed January 24, 2021. http://hdl.handle.net/1969.1/ETD-TAMU-2011-05-9119.

MLA Handbook (7^th Edition):

Woodruff, Matthew Jeffery. “Receptivity Studies on a Swept-Wing Model.” 2012. Web. 24 Jan 2021.

Vancouver:

Woodruff MJ. Receptivity Studies on a Swept-Wing Model. [Internet] [Masters thesis]. Texas A&M University; 2012. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/1969.1/ETD-TAMU-2011-05-9119.

Council of Science Editors:

Woodruff MJ. Receptivity Studies on a Swept-Wing Model. [Masters Thesis]. Texas A&M University; 2012. Available from: http://hdl.handle.net/1969.1/ETD-TAMU-2011-05-9119

Delft University of Technology

26. Groot, K.J. BiGlobal Stability of Shear Flows: Spanwise & Streamwise Analyses.

Degree: 2018, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:60ef07b2-00db-418b-9495-5a9baf6105df ; urn:NBN:nl:ui:24-uuid:60ef07b2-00db-418b-9495-5a9baf6105df ; 60ef07b2-00db-418b-9495-5a9baf6105df ; 10.4233/uuid:60ef07b2-00db-418b-9495-5a9baf6105df ; urn:isbn:978-94-6366-115-7 ; urn:NBN:nl:ui:24-uuid:60ef07b2-00db-418b-9495-5a9baf6105df ; http://resolver.tudelft.nl/uuid:60ef07b2-00db-418b-9495-5a9baf6105df

► Laminar-turbulent transition dictates an increase in skin friction. The resulting turbulent skin friction contributes to approximately 40% of the total drag of commercial aircraft. Reducing… (more)

Subjects/Keywords: Flow instability; measured base flows; Micro-ramp; Swept-wing boundary layer; Crossflow instability; Streamwise BiGlobal problem

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APA (6^th Edition):

Groot, K. J. (2018). BiGlobal Stability of Shear Flows: Spanwise & Streamwise Analyses. (Doctoral Dissertation). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:60ef07b2-00db-418b-9495-5a9baf6105df ; urn:NBN:nl:ui:24-uuid:60ef07b2-00db-418b-9495-5a9baf6105df ; 60ef07b2-00db-418b-9495-5a9baf6105df ; 10.4233/uuid:60ef07b2-00db-418b-9495-5a9baf6105df ; urn:isbn:978-94-6366-115-7 ; urn:NBN:nl:ui:24-uuid:60ef07b2-00db-418b-9495-5a9baf6105df ; http://resolver.tudelft.nl/uuid:60ef07b2-00db-418b-9495-5a9baf6105df

Chicago Manual of Style (16^th Edition):

Groot, K J. “BiGlobal Stability of Shear Flows: Spanwise & Streamwise Analyses.” 2018. Doctoral Dissertation, Delft University of Technology. Accessed January 24, 2021. http://resolver.tudelft.nl/uuid:60ef07b2-00db-418b-9495-5a9baf6105df ; urn:NBN:nl:ui:24-uuid:60ef07b2-00db-418b-9495-5a9baf6105df ; 60ef07b2-00db-418b-9495-5a9baf6105df ; 10.4233/uuid:60ef07b2-00db-418b-9495-5a9baf6105df ; urn:isbn:978-94-6366-115-7 ; urn:NBN:nl:ui:24-uuid:60ef07b2-00db-418b-9495-5a9baf6105df ; http://resolver.tudelft.nl/uuid:60ef07b2-00db-418b-9495-5a9baf6105df.

MLA Handbook (7^th Edition):

Groot, K J. “BiGlobal Stability of Shear Flows: Spanwise & Streamwise Analyses.” 2018. Web. 24 Jan 2021.

Vancouver:

Groot KJ. BiGlobal Stability of Shear Flows: Spanwise & Streamwise Analyses. [Internet] [Doctoral dissertation]. Delft University of Technology; 2018. [cited 2021 Jan 24]. Available from: http://resolver.tudelft.nl/uuid:60ef07b2-00db-418b-9495-5a9baf6105df ; urn:NBN:nl:ui:24-uuid:60ef07b2-00db-418b-9495-5a9baf6105df ; 60ef07b2-00db-418b-9495-5a9baf6105df ; 10.4233/uuid:60ef07b2-00db-418b-9495-5a9baf6105df ; urn:isbn:978-94-6366-115-7 ; urn:NBN:nl:ui:24-uuid:60ef07b2-00db-418b-9495-5a9baf6105df ; http://resolver.tudelft.nl/uuid:60ef07b2-00db-418b-9495-5a9baf6105df.

Council of Science Editors:

Groot KJ. BiGlobal Stability of Shear Flows: Spanwise & Streamwise Analyses. [Doctoral Dissertation]. Delft University of Technology; 2018. Available from: http://resolver.tudelft.nl/uuid:60ef07b2-00db-418b-9495-5a9baf6105df ; urn:NBN:nl:ui:24-uuid:60ef07b2-00db-418b-9495-5a9baf6105df ; 60ef07b2-00db-418b-9495-5a9baf6105df ; 10.4233/uuid:60ef07b2-00db-418b-9495-5a9baf6105df ; urn:isbn:978-94-6366-115-7 ; urn:NBN:nl:ui:24-uuid:60ef07b2-00db-418b-9495-5a9baf6105df ; http://resolver.tudelft.nl/uuid:60ef07b2-00db-418b-9495-5a9baf6105df

27. Carpenter, Andrew L. In-flight Receptivity Experiments on a 30-degree Swept-wing using Micron-sized Discrete Roughness Elements.

Degree: PhD, Aerospace Engineering, 2010, Texas A&M University

URL: http://hdl.handle.net/1969.1/ETD-TAMU-2009-05-728

► One of the last remaining challenges preventing the laminarization of sweptwings is the control of unstable crossflow vortices. In low-disturbance environments the transition from laminar… (more)

▼ One of the last remaining challenges preventing the laminarization of sweptwings is the control of unstable crossflow vortices. In low-disturbance environments the transition from laminar to turbulent flow on the swept-wing initially takes the path of receptivity, where surface roughness or disturbances in the environment introduce shortwavelength disturbances into the boundary layer. This is followed by development and linear growth of stationary crossflow vortices that modify the mean flow, changing the stability characteristics of the boundary layer. Finally, breakdown to turbulence occurs over a short length scale due to the high-frequency secondary instability. The receptivity mechanism is the least understood, yet holds the most promise for providing a laminar flow control strategy. Results of a 3-year flight test program focused on receptivity measurements and laminar flow control on a 30-degree swept-wing are presented. A swept-wing test article was mounted on the port wing of a Cessna O-2A aircraft and operated at a chord Reynolds number of 6.5 to 7.5 million. Spanwise-periodic, micronsized discrete roughness elements were applied at the leading edge of the swept-wing in order to excite the most unstable crossflow wavelength and promote early boundary layer transition. An infrared camera was used to detect boundary-layer transition due to changes in leading-edge roughness. Combined with the IR camera, a new technique of calibrating surface-mounted hotfilms was developed for making disturbance-amplitude measurements downstream of modulated roughness heights. This technique proved to be effective at measuring disturbance amplitudes and can be applied in future tests where instrumentation is limited. Furthermore, laminar flow control was performed with subcritically-spaced roughness. A 100% increase in the region of laminar flow was achieved for some of the conditions tested here. Advisors/Committee Members: Saric, William S. (advisor), Reed, Helen L. (committee member), Ward, Donald T. (committee member), Duggleby, Andrew (committee member).

Subjects/Keywords: Receptivity; Laminar Flow; Boundary Layer; Swept-Wing; Roughness; Hotfilms; Infrared Thermography; Flight Test

…element us Velocity tangential to swept-wing streamline ut Velocity normal to swept-wing… …velocity at swept-wing leading edge Vne Never-exceed speed Vno Top speed in turbulent… …conditions ws Velocity normal to swept-wing streamline wt Spanwise velocity parallel to swept… …wing leading edge zs Spanwise distance along the swept leading edge αt Streamwise… …wavenumber, tangential to swept-wing streamline αto First calculated streamwise growth rate βt…

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APA (6^th Edition):

Carpenter, A. L. (2010). In-flight Receptivity Experiments on a 30-degree Swept-wing using Micron-sized Discrete Roughness Elements. (Doctoral Dissertation). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/ETD-TAMU-2009-05-728

Chicago Manual of Style (16^th Edition):

Carpenter, Andrew L. “In-flight Receptivity Experiments on a 30-degree Swept-wing using Micron-sized Discrete Roughness Elements.” 2010. Doctoral Dissertation, Texas A&M University. Accessed January 24, 2021. http://hdl.handle.net/1969.1/ETD-TAMU-2009-05-728.

MLA Handbook (7^th Edition):

Carpenter, Andrew L. “In-flight Receptivity Experiments on a 30-degree Swept-wing using Micron-sized Discrete Roughness Elements.” 2010. Web. 24 Jan 2021.

Vancouver:

Carpenter AL. In-flight Receptivity Experiments on a 30-degree Swept-wing using Micron-sized Discrete Roughness Elements. [Internet] [Doctoral dissertation]. Texas A&M University; 2010. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/1969.1/ETD-TAMU-2009-05-728.

Council of Science Editors:

Carpenter AL. In-flight Receptivity Experiments on a 30-degree Swept-wing using Micron-sized Discrete Roughness Elements. [Doctoral Dissertation]. Texas A&M University; 2010. Available from: http://hdl.handle.net/1969.1/ETD-TAMU-2009-05-728

28. Hussain, Ali. The Effect of Spanwise Location of an Active Boundary Layer Fence on Swept Wing Performance.

Degree: MS, Aero/Astro Engineering, 2019, The Ohio State University

URL: http://rave.ohiolink.edu/etdc/view?acc_num=osu1555516043121521

► Active flow control (AFC) in the form of a wall normal slot was investigated on a NACA 643-618 laminar wing model. The wing model has… (more)

▼ Active flow control (AFC) in the form of a wall normal slot was investigated on a NACA 643-618 laminar wing model. The wing model has a leading-edge sweep of (Λ = 30°) and tests were performed using a chordwise Reynolds number of 100,000 with a specific focus on the stall characteristics and changes in performance of an AFC slot with spanwise location. The study included comparing a passive boundary layer fence (BLF) and an AFC slot at the same spanwise locations: 0.60z/b, 0.70z/b, and 0.80z/b. Changing the location of the passive BLF resulted in increases in the maximum lift coefficient (CLMax) over the baseline ranging from 10.20-19.30%, with higher gains seen for fences closer to the root. The BLF at 0.60z/b experienced an unstable longitudinal static stability derivative (CMα) at an angle 13° higher than the baseline. Moving the fence outboard to 0.80z/b resulted in delaying this unstable behavior by an additional α=6°. An AFC slot was found to improve upon aspects of the BLF performance at all spanwise locations tested for a Cμ=10.33%. The slot was found to improve CLMax by up to 23.4% at the lowest spanwise location tested (0.60z/b) and this decreased to a 10.6% benefit at 0.80z/b. For the AFC slot, maximum lift performance increased monotonically as more momentum was introduced into the system. In all cases, moving the slot further outboard increased the stall angle. At all spanwise locations, the AFC slot outperformed the BLF in terms of delaying stall and an unstable CMα. Fluorescent tufts were used to visualize the surface flow for the baseline and AFC at all spanwise locations. The results corroborated the load cell findings and helped to visualize separation and spanwise flow at key angles of attack such as stall for the baseline wing. At higher angles of attack, evidence of the AFC slot could clearly be seen in the attached, streamwise flow directly outboard of the fence location. Evidence of a fence and tip vortices were also present for the AFC configurations, explaining the increased lift benefits seen. Advisors/Committee Members: Bons, Jeffrey (Advisor).

Subjects/Keywords: Aerospace Engineering; aerodynamics; active flow control; boundary layer fence; swept wing; experimental; wind tunnel

…control. 1.2 Background Swept wing flow control presents additional challenges when considering… …dimensional wing will stall relatively uniformly along the spanwise direction. In contrast, a swept… …Queijo et al [14] tested numerous wing fence designs on a swept wing (Λ = 35… …investigation into the differences in lift and stability enhancement on a swept wing. To characterize… …which is crucial to studying swept wing aerodynamics [22]. The geometric chord of…

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APA (6^th Edition):

Hussain, A. (2019). The Effect of Spanwise Location of an Active Boundary Layer Fence on Swept Wing Performance. (Masters Thesis). The Ohio State University. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=osu1555516043121521

Chicago Manual of Style (16^th Edition):

Hussain, Ali. “The Effect of Spanwise Location of an Active Boundary Layer Fence on Swept Wing Performance.” 2019. Masters Thesis, The Ohio State University. Accessed January 24, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=osu1555516043121521.

MLA Handbook (7^th Edition):

Hussain, Ali. “The Effect of Spanwise Location of an Active Boundary Layer Fence on Swept Wing Performance.” 2019. Web. 24 Jan 2021.

Vancouver:

Hussain A. The Effect of Spanwise Location of an Active Boundary Layer Fence on Swept Wing Performance. [Internet] [Masters thesis]. The Ohio State University; 2019. [cited 2021 Jan 24]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1555516043121521.

Council of Science Editors:

Hussain A. The Effect of Spanwise Location of an Active Boundary Layer Fence on Swept Wing Performance. [Masters Thesis]. The Ohio State University; 2019. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1555516043121521

RMIT University

29. Guo, D. Modelling and experimental investigations of a bi-modal unmanned underwater/air system.

Degree: 2019, RMIT University

URL: http://researchbank.rmit.edu.au/view/rmit:162852

► The ability to perform underwater and coastal area monitoring missions without surfacing would increase submarine's safety and its combat ability. An innovative bi-modal unmanned/underwater air… (more)

▼ The ability to perform underwater and coastal area monitoring missions without surfacing would increase submarine's safety and its combat ability. An innovative bi-modal unmanned/underwater air system (BUUAS) and its concept of operations (CONOPS) are proposed to reduce the risk of submarine's exposure. The BUUAS is firstly released from a submerged submarine and travels underwater to keep a distance from the submarine. Then it will exit the water using an innovative propulsion system that would allow a transition from water to air with the purpose of carrying out a planned air mission. When the airborne mission is finished, the BUUAS will dive back into the water and cruise to the submarine to be collected. This study aims to design and develop this system that can achieve the proposed CONOPS. The project addresses three critical aspects, namely, i) the study of an optimised configuration considering both aerodynamic and hydrodynamic performance aspects, ii) the exploration for an effective transition between water/air media and iii) the design of the water/air hybrid propulsion system. A variable-sweep wing configuration with a novel wing-deployment mechanism is considered for an efficient operation in water and air. Numerical simulation, water and wind tunnel experimental tests were conducted to assess the performance characteristics of the propulsion unit in water and the aerodynamic characteristics in air. The assessment data supports the feasibility of the bi-modal vehicle configuration and the stability analysis demonstrates the vehicle has static and dynamic stable behaviour during its flight. The water jet transition propulsion system is powered by pressurized CO2 and was developed to enable a fast take-off transition from water to air. The preliminary design covers the system sizing using an analytical model calibrated by the high-fidelity numerical simulation approach and the design of a specialized gas release mechanism adopted in the propulsion unit. The thrust and launch experiments were performed to verify the transition propulsion system design results and applicability. The air and water experimental results of the customized compact hybrid propulsion system confirm its provision of sufficient power for flight and underwater cruise.

Subjects/Keywords: Fields of Research; BUUAS; Transition propulsion system; Hybrid propulsion system; Variable sweep wing configuration; Wind tunnel test; Numerical simulation; Composite materials; Stability analysis

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

APA (6^th Edition):

Guo, D. (2019). Modelling and experimental investigations of a bi-modal unmanned underwater/air system. (Thesis). RMIT University. Retrieved from http://researchbank.rmit.edu.au/view/rmit:162852

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):

Guo, D. “Modelling and experimental investigations of a bi-modal unmanned underwater/air system.” 2019. Thesis, RMIT University. Accessed January 24, 2021. http://researchbank.rmit.edu.au/view/rmit:162852.

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

MLA Handbook (7^th Edition):

Guo, D. “Modelling and experimental investigations of a bi-modal unmanned underwater/air system.” 2019. Web. 24 Jan 2021.

Vancouver:

Guo D. Modelling and experimental investigations of a bi-modal unmanned underwater/air system. [Internet] [Thesis]. RMIT University; 2019. [cited 2021 Jan 24]. Available from: http://researchbank.rmit.edu.au/view/rmit:162852.

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

Council of Science Editors:

Guo D. Modelling and experimental investigations of a bi-modal unmanned underwater/air system. [Thesis]. RMIT University; 2019. Available from: http://researchbank.rmit.edu.au/view/rmit:162852

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

Luleå University of Technology

30. Khan, Fahad Aman. Preliminary aerodynamic investigation of box-wing configurations using low fidelity codes.

Degree: 2010, Luleå University of Technology

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-55530

►

This work outlines the different aerodynamic aspects of box-wing design i.e. an unconventional aircraft design configuration exhibiting the capability of reducing induced drag. Being… (more)

▼

This work outlines the different aerodynamic aspects of box-wing design i.e. an unconventional aircraft design configuration exhibiting the capability of reducing induced drag. Being a nonplanar concept, the basic aerodynamic features differ from conventional designs. To understand these features and their influence on box-wing aerodynamics, parameter variations have been conducted while Munk’s theorem is validated for stagger and sweep. In this process, several important aspects of box- wing are highlighted. An optimization algorithm has been implemented by considering all the design variables collectively to find the global maximum for the box-wing design. All these investigations laid down the important aerodynamic features of box-wing and also proved a method for estimating the reduction in induced drag. To conduct these investigations, vortex lattice methods (VLM) are used. Non planar systems have certain limitations for best operations which provide maximum induced drag reduction. These limitations are examined and applied in the form of constant and specified lift distributions in the analysis. Furthermore, it is concluded that vortex lattice methods do capture the reduction in induced drag correctly if the limitations of span loading are maintained during the analysis. Based on previous results obtained, Euler inviscid analysis for a selected box-wing and a reference wing are carried out. The results of Euler inviscid analysis show good agreement with the results achieved by vortex lattice method in drag reduction. Therefore, VLM methods are capable of analyzing box-wing (and multi planar systems) to a good accuracy. At the same time, transonic airfoil selection is identified as one of the key factors in designing a commercial box-wing aircraft. This study is closed up by discussing different potential advantages for the aviation industry and discusses if a box-wing commercial aircraft should be made reality. On the whole, this work looks into a possible way of investigating futuristic multi planar aircraft configurations by using low fidelity aerodynamic codes.

Validerat; 20101217 (root)

Subjects/Keywords: Technology; Non planar configuration; induced drag reduction; box-wing; aircraft performance; Teknik

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

APA (6^th Edition):

Khan, F. A. (2010). Preliminary aerodynamic investigation of box-wing configurations using low fidelity codes. (Thesis). Luleå University of Technology. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-55530

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):

Khan, Fahad Aman. “Preliminary aerodynamic investigation of box-wing configurations using low fidelity codes.” 2010. Thesis, Luleå University of Technology. Accessed January 24, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-55530.

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

MLA Handbook (7^th Edition):

Khan, Fahad Aman. “Preliminary aerodynamic investigation of box-wing configurations using low fidelity codes.” 2010. Web. 24 Jan 2021.

Vancouver:

Khan FA. Preliminary aerodynamic investigation of box-wing configurations using low fidelity codes. [Internet] [Thesis]. Luleå University of Technology; 2010. [cited 2021 Jan 24]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-55530.

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

Council of Science Editors:

Khan FA. Preliminary aerodynamic investigation of box-wing configurations using low fidelity codes. [Thesis]. Luleå University of Technology; 2010. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-55530

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

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