subject:(wing)

Texas A&M University

1. Cooper, Jacob. Multi-Resolution Simulations of Delta/Diamond Wing Aerodynamics.

Degree: PhD, Aerospace Engineering, 2014, Texas A&M University

URL: http://hdl.handle.net/1969.1/153426

► This dissertation investigates high angle of attack delta wing flow at multiple resolutions of turbulence closure. The work is divided into four studies. The objectives… (more)

▼ This dissertation investigates high angle of attack delta wing flow at multiple resolutions of turbulence closure. The work is divided into four studies. The objectives of each study are: (i) to identify the limits of RANS modeling, (ii) explore the challenges of applying the PANS model to the delta wing flow, (iii) identify the appropriate resolution required to capture specific flow features, and (iv) determine the physical differences between sharp and round leading edge separation. The outcomes from each of these studies are as follows. Steady-state RANS modeling is shown to be adequate for low and moderate angles of attack, except in regions near the point of primary vortex separation. At low Reynolds number the vortex structure on the forward portion of the wing is mostly laminar and must be fully resolved by the grid in order to capture the physics in the aft region. Also at low Reynolds numbers, it is shown that lower resolution simulations perform adequately in capturing important integral flow features such as pressure coefficient and the locations of the vortex separation and attachment lines. High resolution simulations of low Reynolds number flow do resolve more subtle flow features that do not significantly affect the aerodynamic characteristics. The principle advantages of high resolution simulations are most evident at high Reynolds numbers and high angles of attack. The relationship between scale resolution and observed flow features is established. The simulations establish the key flow feature differences between round and sharp leading edge wing at different length scales of motion. Features of interest are the intensity of the vortex structure, the levels of turbulence, surface streamline patterns, and surface pressure coefficient. Differences between the delta and diamond wing shapes are also identified. Advisors/Committee Members: Girimaji, Sharath S (advisor), Cizmas, Paul (committee member), Donzis, Diego (committee member), Chen, Hamn-Ching (committee member).

Subjects/Keywords: delta wing; diamond wing; turbulence model; PANS

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APA (6^th Edition):

Cooper, J. (2014). Multi-Resolution Simulations of Delta/Diamond Wing Aerodynamics. (Doctoral Dissertation). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/153426

Chicago Manual of Style (16^th Edition):

Cooper, Jacob. “Multi-Resolution Simulations of Delta/Diamond Wing Aerodynamics.” 2014. Doctoral Dissertation, Texas A&M University. Accessed January 25, 2021. http://hdl.handle.net/1969.1/153426.

MLA Handbook (7^th Edition):

Cooper, Jacob. “Multi-Resolution Simulations of Delta/Diamond Wing Aerodynamics.” 2014. Web. 25 Jan 2021.

Vancouver:

Cooper J. Multi-Resolution Simulations of Delta/Diamond Wing Aerodynamics. [Internet] [Doctoral dissertation]. Texas A&M University; 2014. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1969.1/153426.

Council of Science Editors:

Cooper J. Multi-Resolution Simulations of Delta/Diamond Wing Aerodynamics. [Doctoral Dissertation]. Texas A&M University; 2014. Available from: http://hdl.handle.net/1969.1/153426

NSYSU

2. Pan, Chih-Hong. A Preliminary Study of Left Wing in Taiwan - from the Perspective of Historical Institutionalism.

Degree: Master, Political Science, 2018, NSYSU

URL: http://etd.lib.nsysu.edu.tw/ETD-db/ETD-search/view_etd?URN=etd-0702118-104150

► With the theme of " why did Taiwan not yet have a strong left-wing party?", this paper analyzes the factors behind it and also analyzes… (more)

▼ With the theme of " why did Taiwan not yet have a strong left-wing party?", this paper analyzes the factors behind it and also analyzes the left wing party history of Taiwan through its four periods. The first period, the period of Taisho democracy. The enlightenment and development of Taiwan's left wing (1920-1931). The left wing had been initiated in this period, but eventually turned into underground activity because of mass arrest of left wing activist by Japanese police, highlighting the asymmetric relationship between the colonizer and the colonized; the second period, the martial law period in Kuomintang Government-ruled Taiwan (1945-1987). At this stage, the Taiwanese left-wing experienced destruction and blankness. The Kuomintang Government implemented the martial law. The left wing of Taiwan was completely eliminated, and the ideological inheritance and actions of the left wing were lost, it resulting in the "left-wing fault " and the rise of ânational consciousness" in Taiwan. It highlights the state's institutional dependence on legal violent rule; in the third period, overseas Baodiao movement promoted the opportunity for Taiwan's left-wing resurgence (1970); in the fourth period, why, not yet, Taiwan has a strong left-wing party? (1987-2016). From the interaction between Taiwanese leftist and the national system of the first three periods mentioned above, plus the economic structure of Taiwan in the fourth period and the current state of the social class, we can summarize into four aspects why Taiwan has not yet a strong leftist party, (1) institutional path dependence and power inequalities. Two repressions in history caused the "Taiwan Left Wing Fault"ãlost of left-wing philosophy and action tradition; (2) The system affected actors' preferences. Causing democracy and national consciousness to prioritize class consciousness; (3) Economic development has priority. Focus on economic growth and ignore social distribution; (4) Stable social class. Taiwanâs income distribution creates stable middle class. While analyzing the above factors, this paper attempts to find out the conditions for the emergence of strong leftist parties in Taiwan. These conditions are just preliminary discussion. I hope that some materials from discussion will provide a little help to left-wing personnel in Taiwan who still seek for a development model. Advisors/Committee Members: Lin, Wen-Pin (chair), Liao, Da-Chi (committee member), Dzeng, Yi-Ren (chair).

Subjects/Keywords: class consciousness; left-wing; left-wing party

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APA (6^th Edition):

Pan, C. (2018). A Preliminary Study of Left Wing in Taiwan - from the Perspective of Historical Institutionalism. (Thesis). NSYSU. Retrieved from http://etd.lib.nsysu.edu.tw/ETD-db/ETD-search/view_etd?URN=etd-0702118-104150

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):

Pan, Chih-Hong. “A Preliminary Study of Left Wing in Taiwan - from the Perspective of Historical Institutionalism.” 2018. Thesis, NSYSU. Accessed January 25, 2021. http://etd.lib.nsysu.edu.tw/ETD-db/ETD-search/view_etd?URN=etd-0702118-104150.

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

MLA Handbook (7^th Edition):

Pan, Chih-Hong. “A Preliminary Study of Left Wing in Taiwan - from the Perspective of Historical Institutionalism.” 2018. Web. 25 Jan 2021.

Vancouver:

Pan C. A Preliminary Study of Left Wing in Taiwan - from the Perspective of Historical Institutionalism. [Internet] [Thesis]. NSYSU; 2018. [cited 2021 Jan 25]. Available from: http://etd.lib.nsysu.edu.tw/ETD-db/ETD-search/view_etd?URN=etd-0702118-104150.

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

Council of Science Editors:

Pan C. A Preliminary Study of Left Wing in Taiwan - from the Perspective of Historical Institutionalism. [Thesis]. NSYSU; 2018. Available from: http://etd.lib.nsysu.edu.tw/ETD-db/ETD-search/view_etd?URN=etd-0702118-104150

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

University of Manchester

3. Abdul Hamid, Mohd Faisal. Aerodynamic models for insect flight.

Degree: PhD, 2016, University of Manchester

URL: https://www.research.manchester.ac.uk/portal/en/theses/aerodynamic-models-for-insect-flight(057be27b-265a-45a0-b8d0-dc3c02a62a77).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.728093

► Numerical models of insect flapping flight have previously been developed and used to simulate the performance of insect flight. These models were commonly developed via… (more)

▼ Numerical models of insect flapping flight have previously been developed and used to simulate the performance of insect flight. These models were commonly developed via Blade Element Theory, offering efficient computation, thus allowing them to be coupled with optimisation procedures for predicting optimal flight. However, the models have only been used for simulating hover flight, and often neglect the presence of the induced flow effect. Although some models account for the induced flow effect, the rapid changes of this effect on each local wing element have not been modelled. Crucially, this effect appears in both axial and radial directions, which influences the direction and magnitude of the incoming air, and hence the resulting aerodynamic forces. This thesis describes the development of flapping wing models aimed at advancing theoretical tools for simulating the optimum performance of insect flight. Two models are presented: single and tandem wing configurations for hawk moth and dragonfly, respectively. These models are designed by integrating a numerical design procedure to account for the induced flow effects. This approach facilitates the determination of the instantaneous relative velocity at any given spanwise location on the wing, following the changes of the axial and radial induced flow effects on the wing. For the dragonfly, both wings are coupled to account for the interaction of the flow, particularly the fact that the hindwing operates in the slipstream of the forewing. A heuristic optimisation procedure (particle swarming) is used to optimise the stroke or the wing kinematics at all flight conditions (hover, level, and accelerating flight). The cost function is the propulsive efficiency coupled with constraints for flight stability. The vector of the kinematic variables consists of up to 28 independent parameters (14 per wing for a dragonfly), each with a constrained range derived from the maximum available power, the flight muscle ratio, and the kinematics of real insects; this will prevent physically-unrealistic solutions of the wing motion. The model developed in this thesis accounts for the induced flow, and eliminates the dependency on the empirical translation lift coefficient. Validations are shown with numerical simulations for the hover case, and with experimental results for the forward flight case. From the results obtained, the effect of the induced velocity is found to be greatest in the middle of the stroke. The use of an optimisation process is shown to greatly improve the flapping kinematics, resulting in low power consumption in all flight conditions. In addition, a study on dragonfly flight has shown that the maximum acceleration is dependent on the size of the flight muscle.

Subjects/Keywords: 629.13; flapping wing; insect flight; tandem wing

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

APA (6^th Edition):

Abdul Hamid, M. F. (2016). Aerodynamic models for insect flight. (Doctoral Dissertation). University of Manchester. Retrieved from https://www.research.manchester.ac.uk/portal/en/theses/aerodynamic-models-for-insect-flight(057be27b-265a-45a0-b8d0-dc3c02a62a77).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.728093

Chicago Manual of Style (16^th Edition):

Abdul Hamid, Mohd Faisal. “Aerodynamic models for insect flight.” 2016. Doctoral Dissertation, University of Manchester. Accessed January 25, 2021. https://www.research.manchester.ac.uk/portal/en/theses/aerodynamic-models-for-insect-flight(057be27b-265a-45a0-b8d0-dc3c02a62a77).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.728093.

MLA Handbook (7^th Edition):

Abdul Hamid, Mohd Faisal. “Aerodynamic models for insect flight.” 2016. Web. 25 Jan 2021.

Vancouver:

Abdul Hamid MF. Aerodynamic models for insect flight. [Internet] [Doctoral dissertation]. University of Manchester; 2016. [cited 2021 Jan 25]. Available from: https://www.research.manchester.ac.uk/portal/en/theses/aerodynamic-models-for-insect-flight(057be27b-265a-45a0-b8d0-dc3c02a62a77).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.728093.

Council of Science Editors:

Abdul Hamid MF. Aerodynamic models for insect flight. [Doctoral Dissertation]. University of Manchester; 2016. Available from: https://www.research.manchester.ac.uk/portal/en/theses/aerodynamic-models-for-insect-flight(057be27b-265a-45a0-b8d0-dc3c02a62a77).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.728093

University of Manchester

4. Abdul Hamid, Mohd Faisal Bin. Aerodynamic models for insect flight.

Degree: 2016, University of Manchester

URL: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:303191

► Numerical models of insect flapping flight have previously been developed and used to simulate the performance of insect flight. These models were commonly developed via… (more)

▼ Numerical models of insect flapping flight have previously been developed and used to simulate the performance of insect flight. These models were commonly developed via Blade Element Theory, offering efficient computation, thus allowing them to be coupled with optimisation procedures for predicting optimal flight. However, the models have only been used for simulating hover flight, and often neglect the presence of the induced flow effect. Although some models account for the induced flow effect, the rapid changes of this effect on each local wing element have not been modelled. Crucially, this effect appears in both axial and radial directions, which influences the direction and magnitude of the incoming air, and hence the resulting aerodynamic forces.This thesis describes the development of flapping wing models aimed at advancing theoretical tools for simulating the optimum performance of insect flight. Two models are presented: single and tandem wing configurations for hawk moth and dragonfly, respectively. These models are designed by integrating a numerical design procedure to account for the induced flow effects. This approach facilitates the determination of the instantaneous relative velocity at any given spanwise location on the wing, following the changes of the axial and radial induced flow effects on the wing. For the dragonfly, both wings are coupled to account for the interaction of the flow, particularly the fact that the hindwing operates in the slipstream of the forewing.A heuristic optimisation procedure (particle swarming) is used to optimise the stroke or the wing kinematics at all flight conditions (hover, level, and accelerating flight). The cost function is the propulsive efficiency coupled with constraints for flight stability. The vector of the kinematic variables consists of up to 28 independent parameters (14 per wing for a dragonfly), each with a constrained range derived from the maximum available power, the flight muscle ratio, and the kinematics of real insects; this will prevent physically-unrealistic solutions of the wing motion. The model developed in this thesis accounts for the induced flow, and eliminates the dependency on the empirical translation lift coefficient. Validations are shown with numerical simulations for the hover case, and with experimental results for the forward flight case. From the results obtained, the effect of the induced velocity is found to be greatest in the middle of the stroke. The use of an optimisation process is shown to greatly improve the flapping kinematics, resulting in low power consumption in all flight conditions. In addition, a study on dragonfly flight has shown that the maximum acceleration is dependent on the size of the flight muscle. Advisors/Committee Members: IACOVIDES, HECTOR H, Iacovides, Hector, Filippone, Antonino.

Subjects/Keywords: flapping wing; insect flight; tandem wing

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

APA (6^th Edition):

Abdul Hamid, M. F. B. (2016). Aerodynamic models for insect flight. (Doctoral Dissertation). University of Manchester. Retrieved from http://www.manchester.ac.uk/escholar/uk-ac-man-scw:303191

Chicago Manual of Style (16^th Edition):

Abdul Hamid, Mohd Faisal Bin. “Aerodynamic models for insect flight.” 2016. Doctoral Dissertation, University of Manchester. Accessed January 25, 2021. http://www.manchester.ac.uk/escholar/uk-ac-man-scw:303191.

MLA Handbook (7^th Edition):

Abdul Hamid, Mohd Faisal Bin. “Aerodynamic models for insect flight.” 2016. Web. 25 Jan 2021.

Vancouver:

Abdul Hamid MFB. Aerodynamic models for insect flight. [Internet] [Doctoral dissertation]. University of Manchester; 2016. [cited 2021 Jan 25]. Available from: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:303191.

Council of Science Editors:

Abdul Hamid MFB. Aerodynamic models for insect flight. [Doctoral Dissertation]. University of Manchester; 2016. Available from: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:303191

University of Kansas

5. Brown, Matthew Alan. A Computational Method for Determining Distributed Aerodynamic Loads on Planforms of Arbitrary Shape in Compressible Subsonic Flow.

Degree: MS, Aerospace Engineering, 2013, University of Kansas

URL: http://hdl.handle.net/1808/14195

► The methods presented in this work are intended to provided an easy to understand and easy to apply method for determining the distributed aerodynamic loads… (more)

Subjects/Keywords: Aerospace engineering; Aerodyanmic loads; Cranked wing; Wing aerodyanmics; Wing loads

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APA (6^th Edition):

Brown, M. A. (2013). A Computational Method for Determining Distributed Aerodynamic Loads on Planforms of Arbitrary Shape in Compressible Subsonic Flow. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/14195

Chicago Manual of Style (16^th Edition):

Brown, Matthew Alan. “A Computational Method for Determining Distributed Aerodynamic Loads on Planforms of Arbitrary Shape in Compressible Subsonic Flow.” 2013. Masters Thesis, University of Kansas. Accessed January 25, 2021. http://hdl.handle.net/1808/14195.

MLA Handbook (7^th Edition):

Brown, Matthew Alan. “A Computational Method for Determining Distributed Aerodynamic Loads on Planforms of Arbitrary Shape in Compressible Subsonic Flow.” 2013. Web. 25 Jan 2021.

Vancouver:

Brown MA. A Computational Method for Determining Distributed Aerodynamic Loads on Planforms of Arbitrary Shape in Compressible Subsonic Flow. [Internet] [Masters thesis]. University of Kansas; 2013. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/14195.

Council of Science Editors:

Brown MA. A Computational Method for Determining Distributed Aerodynamic Loads on Planforms of Arbitrary Shape in Compressible Subsonic Flow. [Masters Thesis]. University of Kansas; 2013. Available from: http://hdl.handle.net/1808/14195

Linköping University

6. Sohaib, Muhammad. Parameterized Automated Generic Model for Aircraft Wing Structural Design and Mesh Generation for Finite Element Analysis.

Degree: Machine Design, 2011, Linköping University

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-71264

► This master thesis work presents the development of a parameterized automated generic model for the structural design of an aircraft wing. Furthermore, in order… (more)

Subjects/Keywords: aircraft design; aircraft wing; wing spars; wing ribs; FEM; structural mesh; generic wing model; parametric wing model; automation; design; TECHNOLOGY; TEKNIKVETENSKAP

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APA (6^th Edition):

Sohaib, M. (2011). Parameterized Automated Generic Model for Aircraft Wing Structural Design and Mesh Generation for Finite Element Analysis. (Thesis). Linköping University. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-71264

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):

Sohaib, Muhammad. “Parameterized Automated Generic Model for Aircraft Wing Structural Design and Mesh Generation for Finite Element Analysis.” 2011. Thesis, Linköping University. Accessed January 25, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-71264.

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

MLA Handbook (7^th Edition):

Sohaib, Muhammad. “Parameterized Automated Generic Model for Aircraft Wing Structural Design and Mesh Generation for Finite Element Analysis.” 2011. Web. 25 Jan 2021.

Vancouver:

Sohaib M. Parameterized Automated Generic Model for Aircraft Wing Structural Design and Mesh Generation for Finite Element Analysis. [Internet] [Thesis]. Linköping University; 2011. [cited 2021 Jan 25]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-71264.

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

Council of Science Editors:

Sohaib M. Parameterized Automated Generic Model for Aircraft Wing Structural Design and Mesh Generation for Finite Element Analysis. [Thesis]. Linköping University; 2011. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-71264

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

Carnegie Mellon University

7. Colmenares, David. Design and Control of a Resonant, Flapping Wing Micro Aerial Vehicle Capable of Controlled Flight.

Degree: 2017, Carnegie Mellon University

URL: http://repository.cmu.edu/dissertations/1032

► Small scale unmanned aircraft, such as quadrotors, that are quickly emerging as versatile tools for a wide range of applications including search and rescue, hazardous… (more)

▼ Small scale unmanned aircraft, such as quadrotors, that are quickly emerging as versatile tools for a wide range of applications including search and rescue, hazardous environment exploration, or just shooting great video, are known as micro air vehicles (MAVs). However, for millimeter scale vehicles with weights under 10 grams, conventional flight technologies become greatly inefficient and instead inspiration is drawn from biology. Flapping wing MAVs (FWMAVs) have been created based on insects and hummingbirds in an effort to emulate their extreme agility and ability to hover in place. FWMAVs possess unique capabilities in terms of maneuverability, small size, and ability to operate in dynamic environments that make them particularly well suited for environmental monitoring and swarm applications such as artificial crop pollination. Despite their advantages, significant challenges in fabrication, power, and control must be overcome in order to make FWMAVs a reliable platform. Current designs suffer from high mechanical complexity and often rely on off-board power, sensing, and control, which compromises their autonomy and limits practical applications. The goal of my research is to develop a simple FWMAV design that provides high efficiency and controllability. An efficient, simple, and controllable vehicle design is developed utilizing the principles of resonance, emulation of biological flight control, and under-actuation. A highly efficient, resonant actuator is achieved by attaching a spring in parallel to the output shaft of a commercial geared DC micro-motor. This actuator directly drives the wings of the vehicle, allowing them to be controlled precisely and independently. This direct control strategy emulates biology and differs from other FWMAV designs that utilize complicated transmissions to generate flapping from rotary motor output. Direct control of the wings allows for emulation of biological wing kinematics, resulting in control based on wing motion alone. Furthermore, under-actuation is employed to mimic the rotational motion of insect wings. A rotational joint is added between the motor and wing membrane such that the wing rotates passively in response to aerodynamic forces that are generated as the wing is driven. This design is realized in several stages, initial prototyping, simulation and development of the actuator and wings, then finally a control system is developed. First the system was modeled and improved experimentally in order to achieve lift off. Improvements to the actuator were realized through component variation and custom fabrication increasing torque and power density by 161.1% and 666.8% respectively compared to the gearmotor alone and increased the resonant operating frequency of the vehicle from 4 Hz to 23 Hz. Advances in wing fabrication allowed for flexible wings that increased translational lift production by 35.3%, aerodynamic efficiency by 41.3%, and the effective lift coefficient by 63.7% with dynamic twisting. A robust control architecture was then developed iteratively…

Subjects/Keywords: Micro Aerial Vehicle; Flapping wing; Resonant Actuator; DC motor; Thermal Model; Flexible Wing; Wing Twist

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

APA (6^th Edition):

Colmenares, D. (2017). Design and Control of a Resonant, Flapping Wing Micro Aerial Vehicle Capable of Controlled Flight. (Thesis). Carnegie Mellon University. Retrieved from http://repository.cmu.edu/dissertations/1032

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):

Colmenares, David. “Design and Control of a Resonant, Flapping Wing Micro Aerial Vehicle Capable of Controlled Flight.” 2017. Thesis, Carnegie Mellon University. Accessed January 25, 2021. http://repository.cmu.edu/dissertations/1032.

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

MLA Handbook (7^th Edition):

Colmenares, David. “Design and Control of a Resonant, Flapping Wing Micro Aerial Vehicle Capable of Controlled Flight.” 2017. Web. 25 Jan 2021.

Vancouver:

Colmenares D. Design and Control of a Resonant, Flapping Wing Micro Aerial Vehicle Capable of Controlled Flight. [Internet] [Thesis]. Carnegie Mellon University; 2017. [cited 2021 Jan 25]. Available from: http://repository.cmu.edu/dissertations/1032.

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

Council of Science Editors:

Colmenares D. Design and Control of a Resonant, Flapping Wing Micro Aerial Vehicle Capable of Controlled Flight. [Thesis]. Carnegie Mellon University; 2017. Available from: http://repository.cmu.edu/dissertations/1032

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

University of Manchester

8. El Ouardi, Othman. Design, Analysis And Testing Of An Aircraft Wing Model With Morphing Mechanism.

Degree: 2014, University of Manchester

URL: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:237682

► Wing morphing has the potential to significantly improve the performance of an aircraft. The aerospace industry currently relies on control surfaces for changing aircraft wing… (more)

▼ Wing morphing has the potential to significantly improve the performance of an aircraft. The aerospace industry currently relies on control surfaces for changing aircraft wing geometry for different parts of the flight envelope. The needs for reduced fuel consumption and improved flight capability are motivating the aerospace industry to explore alternatives such as wing morphing. Based on this premise, the design, analysis and testing of an aircraft wing model with morphing mechanism is presented. A design study was initially performed to verify the feasibility of the adaptive wing to entirely actuate using shape memory alloy wires (SMA). Finite element method (FEM) was used to assess the capability of the wing to withstand the aerodynamic load and to morph to a desired shape. The actuators’ forces and displacements were also evaluated by finite element simulation.The airframe of a morphing wing, consisting of two ribs made of 14 segments and interconnected through torsional stiffened hinges, was developed. The two ribs were connected through spars with circular cross sections. In the simulation, a skin was considered as the overlapping sliding segments. Morphing of the wing was achieved by displacement of a designed linkage mechanism, using SMA wires installed inside the airframe. The SMA wires connect the front spar to the linkage mechanism via mounting brackets. Torsional and gas springs were considered for providing counter-resisting forces to the system. Actuation occurred by heating the SMA wires through continuous feeding of electric current.Finally, a prototype with rectangular plan section was manufactured and tested so as to demonstrate the morphing capability of the conceived structural layout. The results of the functional test showed high correlation levels with respect to numerical predictions, thus validating the modelling approaches implemented during the design phase. The wing appears to deform smoothly with the induction of very small stresses. A change in thickness ratio of up to 200 % was first achieved through static loading with a total force of 90 N. A 55 mm displacement of the linkage mechanism transformed the model from NACA 0012 to NACA 0036. A total of 4 SMA wires (2 wires per bundle) provided the force required to actuate the test demonstrator up to half the morphing intended. The strain on the wires was limited to 3.5 % to allow a complete shape recovery. This thesis presents the methodology and the results obtained from designing building and testing the proposed wing-morphing model. Advisors/Committee Members: Oyadiji, Sunday.

Subjects/Keywords: Morphing wing; Adaptive wing; SMA; Variable thickness wing; Shape morphing; Smart materials

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

APA (6^th Edition):

El Ouardi, O. (2014). Design, Analysis And Testing Of An Aircraft Wing Model With Morphing Mechanism. (Doctoral Dissertation). University of Manchester. Retrieved from http://www.manchester.ac.uk/escholar/uk-ac-man-scw:237682

Chicago Manual of Style (16^th Edition):

El Ouardi, Othman. “Design, Analysis And Testing Of An Aircraft Wing Model With Morphing Mechanism.” 2014. Doctoral Dissertation, University of Manchester. Accessed January 25, 2021. http://www.manchester.ac.uk/escholar/uk-ac-man-scw:237682.

MLA Handbook (7^th Edition):

El Ouardi, Othman. “Design, Analysis And Testing Of An Aircraft Wing Model With Morphing Mechanism.” 2014. Web. 25 Jan 2021.

Vancouver:

El Ouardi O. Design, Analysis And Testing Of An Aircraft Wing Model With Morphing Mechanism. [Internet] [Doctoral dissertation]. University of Manchester; 2014. [cited 2021 Jan 25]. Available from: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:237682.

Council of Science Editors:

El Ouardi O. Design, Analysis And Testing Of An Aircraft Wing Model With Morphing Mechanism. [Doctoral Dissertation]. University of Manchester; 2014. Available from: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:237682

Indian Institute of Science

9. Mukherjee, Sujoy. Structural Modeling And Analysis Of Insect Scale Flapping Wing.

Degree: PhD, Faculty of Engineering, 2013, Indian Institute of Science

URL: http://etd.iisc.ac.in/handle/2005/2021

► Micro Air Vehicles (MAVs) are defined as a class of vehicles with their larger dimension not exceeding 15 cm and weighing 100 gm. The three… (more)

▼ Micro Air Vehicles (MAVs) are defined as a class of vehicles with their larger dimension not exceeding 15 cm and weighing 100 gm. The three main approaches for providing lift for such vehicles are through fixed, rotating and flapping wings. The flapping wing MAVs are more efficient in the low Reynolds-number regime than conventional wings and rotors. Natural flapping ﬂyers, such as birds and insects, serve as a natural source of inspiration for the development of MAV. Flapping wing design is one of the major challenges to develop an MAV because it is not only responsible for the lift, but also propulsion and maneuvers. Two important issues are addressed in this thesis: (1) an equivalent beam-type modeling of actual insect wing is proposed based on the experimental data and (2) development of the numerical framework for design and analysis of insect scale smart flapping wing. The experimental data is used for structural modeling of the blowfly Calliphora wing as a stepped cantilever beam with nine spanwise sections of varying mass per unit lengths, flexural rigidity (EI) and torsional rigidity (GJ) values. Natural frequencies, both in bending and torsion, are obtained by solving the homogeneous part of the respective governing differential equations using the finite element method. It is found that natural frequency in bending and torsion are 3.17 and 1.57 times higher than flapping frequency of Calliphora wing, respectively. The results provide guidelines for the biomimetic structural design of insect-scale flapping wings. In addition to the structural modeling of the insect wing, development of the biomimetic mechanisms played a very important role to achieve a deeper insight of the flapping ﬂight. Current biomimetic flapping wing mechanisms are either dynamically scaled or rely on pneumatic and motor-driven flapping actuators. Unfortunately, these mechanisms become bulky and flap at very low frequency. Moreover, mechanisms designed with conventional actuators lead to high weight and system-complexity which makes it difficult to mimic the complex wingbeat kinematics of the natural flyers. The usage of the actuator made of smart materials such as ionic polymer metal composites (IPMCs) and piezoceramics to design flapping wings is a potential alternative. IPMCs are a relatively new type of smart material that belongs to the family of Electroactive Polymers (EAP) which is also known as “artificial muscles”. In this work, structural modeling and aerodynamic analysis of a dragonﬂy inspired IPMC flapping wing are performed using numerical simulations. An optimization study is performed to obtain improved flapping actuation of the IPMC wing. Later, a comparative study of the performances of three IPMC flapping wings having the same size as the actual wings of three different dragonﬂy species Aeshna Multicolor, Anax Parthenope Julius and Sympetrum Frequens is conducted. It is found that the IPMC wing generates sufficient lift to support its own weight and carry a small payload. In addition to the IPMC, piezoelectric… Advisors/Committee Members: Ganguli, Ranjan (advisor).

Subjects/Keywords: Flapping Wing; Micro Air Vehicles (MAVs); Calliphora Wing; Flapping Wings; Twisting Wing; Flapping Flight; Aeronautics

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

APA (6^th Edition):

Mukherjee, S. (2013). Structural Modeling And Analysis Of Insect Scale Flapping Wing. (Doctoral Dissertation). Indian Institute of Science. Retrieved from http://etd.iisc.ac.in/handle/2005/2021

Chicago Manual of Style (16^th Edition):

Mukherjee, Sujoy. “Structural Modeling And Analysis Of Insect Scale Flapping Wing.” 2013. Doctoral Dissertation, Indian Institute of Science. Accessed January 25, 2021. http://etd.iisc.ac.in/handle/2005/2021.

MLA Handbook (7^th Edition):

Mukherjee, Sujoy. “Structural Modeling And Analysis Of Insect Scale Flapping Wing.” 2013. Web. 25 Jan 2021.

Vancouver:

Mukherjee S. Structural Modeling And Analysis Of Insect Scale Flapping Wing. [Internet] [Doctoral dissertation]. Indian Institute of Science; 2013. [cited 2021 Jan 25]. Available from: http://etd.iisc.ac.in/handle/2005/2021.

Council of Science Editors:

Mukherjee S. Structural Modeling And Analysis Of Insect Scale Flapping Wing. [Doctoral Dissertation]. Indian Institute of Science; 2013. Available from: http://etd.iisc.ac.in/handle/2005/2021

University of Rochester

10. Loehlin, David Walker (1981 - ); Werren, John H. Genetics of size and shape evolution in Nasonia.

Degree: PhD, 2012, University of Rochester

URL: http://hdl.handle.net/1802/19345

► My research addresses a fundamental question in biology: What genes and genetic changes are responsible for size and shape differences between species? In Chapter 1,… (more)

▼ My research addresses a fundamental question in biology: What genes and genetic changes are responsible for size and shape differences between species? In Chapter 1, I review the genetics of growth and what patterns might be found in the genetic changes that underlie the evolution of size and shape differences. While much is known about growth-regulating genes and their roles in human disease, one aspect is not well understood: which parts of the growth gene network specify the sizes and shapes of organs. Naturally occurring differences in size and shape, especially species differences, can be used to answer this question. An analysis of the small number of studies of organ size evolution, including my own work, points to a prominent role for cis-regulatory changes to signaling genes. This suggests that these upstream parts of the growth gene network are where many aspects of size and shape are specified. I next focus on determining the genetic basis of huge differences in wing size between two closely related wasps, Nasonia vitripennis and N. giraulti. In Chapter 2, I (along with collaborators) identify the genetic basis of the wing-size1 (ws1) quantitative trait locus (QTL), which changes Nasonia male wing area by 45% with no effect on females. Ws1 maps to a noncoding cis-regulatory element adjacent to the doublesex (dsx) gene and causes wing-specific changes in dsx expression. The capacity for cis-regulatory elements to give a gene new sex- and tissue-specific expression may explain how a conserved sex-signaling gene became recruited to regulate organ size. Chapters 3 and 4 focus on a Nasonia wing shape QTL, widerwing (wdw). In Chapter 3 I report the identification, morphological effects and evolution of wdw in four Nasonia species. In Chapter 4 I report the genetic basis of wdw. The wdw QTL maps down to one gene: the wasp version of unpaired (upd), a Drosophila cell-proliferation regulator in the JAK/STAT signaling pathway. Multiple changes around this upd-like gene are involved, each of which causes spatiotemporal differences in upd-like expression and corresponding spatial changes in wing size, revealing that wdw is a hotspot of wing size evolution.

Subjects/Keywords: Doublesex; Morphology; Unpaired; Wing

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APA (6^th Edition):

Loehlin, David Walker (1981 - ); Werren, J. H. (2012). Genetics of size and shape evolution in Nasonia. (Doctoral Dissertation). University of Rochester. Retrieved from http://hdl.handle.net/1802/19345

Chicago Manual of Style (16^th Edition):

Loehlin, David Walker (1981 - ); Werren, John H. “Genetics of size and shape evolution in Nasonia.” 2012. Doctoral Dissertation, University of Rochester. Accessed January 25, 2021. http://hdl.handle.net/1802/19345.

MLA Handbook (7^th Edition):

Loehlin, David Walker (1981 - ); Werren, John H. “Genetics of size and shape evolution in Nasonia.” 2012. Web. 25 Jan 2021.

Vancouver:

Loehlin, David Walker (1981 - ); Werren JH. Genetics of size and shape evolution in Nasonia. [Internet] [Doctoral dissertation]. University of Rochester; 2012. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1802/19345.

Council of Science Editors:

Loehlin, David Walker (1981 - ); Werren JH. Genetics of size and shape evolution in Nasonia. [Doctoral Dissertation]. University of Rochester; 2012. Available from: http://hdl.handle.net/1802/19345

Delft University of Technology

11. Riahi, G. (author). Model Order Reduction for a Nonlinear Finite Element Model of a Joined Wing Structure.

Degree: 2012, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:ab0d4288-3dfd-468d-a6d8-cdafa3ea2164

►

Joined Wing is a concept of nonplanar airplane wing structure. This is a new concept which is not yet used for commercial airplanes but has… (more)

Subjects/Keywords: nonlinear; finite; wing structure

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APA (6^th Edition):

Riahi, G. (. (2012). Model Order Reduction for a Nonlinear Finite Element Model of a Joined Wing Structure. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:ab0d4288-3dfd-468d-a6d8-cdafa3ea2164

Chicago Manual of Style (16^th Edition):

Riahi, G (author). “Model Order Reduction for a Nonlinear Finite Element Model of a Joined Wing Structure.” 2012. Masters Thesis, Delft University of Technology. Accessed January 25, 2021. http://resolver.tudelft.nl/uuid:ab0d4288-3dfd-468d-a6d8-cdafa3ea2164.

MLA Handbook (7^th Edition):

Riahi, G (author). “Model Order Reduction for a Nonlinear Finite Element Model of a Joined Wing Structure.” 2012. Web. 25 Jan 2021.

Vancouver:

Riahi G(. Model Order Reduction for a Nonlinear Finite Element Model of a Joined Wing Structure. [Internet] [Masters thesis]. Delft University of Technology; 2012. [cited 2021 Jan 25]. Available from: http://resolver.tudelft.nl/uuid:ab0d4288-3dfd-468d-a6d8-cdafa3ea2164.

Council of Science Editors:

Riahi G(. Model Order Reduction for a Nonlinear Finite Element Model of a Joined Wing Structure. [Masters Thesis]. Delft University of Technology; 2012. Available from: http://resolver.tudelft.nl/uuid:ab0d4288-3dfd-468d-a6d8-cdafa3ea2164

Delft University of Technology

12. Rousseau, Rob (author). Semi-Analytical Closed-Wing Weight Estimation during Conceptual Design.

Degree: 2017, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:948ab573-cea8-43a7-af94-40a38994016b

► One of the novel configurations that could revolutionize the aviation industry is the PrandtlPlane. The closed-wing design features a low front wing and a high… (more)

▼ One of the novel configurations that could revolutionize the aviation industry is the PrandtlPlane. The closed-wing design features a low front wing and a high rear wing, connected by a lateral surface. In this research, the rear wings of the configuration are attached to a set of fins. Previous conceptual closed-wing design studies have failed to accurately predict the wing weight of the configuration, by using empirical relations or semi-analytical methods designed for conventional wings. These methods fail to capture the three major structural characteristics of a closed-wing design: an over-constrained structure, significant secondary bending moments and shear forces, and a different lay-out of the constraints definition. Therefore, a semi-analytical closed-wing weight estimator was developed. The primary weight is estimated analytically, while the secondary weights are defined by empirical relations. The primary structure is sized using an equivalent beam method, which is designed to withstand the aerodynamic, inertial and fuel loads applied to the structure. The aerodynamic loads are estimated with a vortex lattice method, at a 2.5g pull-up manoeuvre. For the PrandtlPlane configuration, the fin is modelled as a support to the rear wing. Due to the over-constrained nature of the structure, a stiffness iteration loop is implemented in which the internal loads are determined using the displacement method and all cross-sections are sized. The cross-sectional design features four booms, which are cross-coupled and four skins, which are sized independently. A total weight estimation of a closed-wing design takes 20-30 seconds. Sensitivity analyses are performed to establish the main drivers of the total wing weight and its distribution. Wingspan, wing sweep angle, fin sweep angle and longitudinal center of gravity position were determined to have the most influence on the total wing weight and its distribution. The new tool was implemented in the conceptual design workflow of the Initiator. A comparison between a design study in the Initiator with the closed-wing weight estimator and the previous methodology showed large discrepancies. Three design studies were performed with missions varying in payload weight, number of passengers and range. The total offset in the wing weight between the two methods ranged from 4.5% to 30.4%, leading to discrepancies in the required fuel mass of 1.6% and 5.7% respectively. Apart from the large offsets in total wing weight, the previous methodology also failed to accurately predict the distribution of the weight between the front, rear and lateral wing. Furthermore, the offsets between the methodologies are case-dependent and no clear relationship between them can be distinguished. Future conceptual design studies should thus include a closed-wing weight estimator. Finally, a parametric study was performed to identify the effect of altering the wing area ratio between the front and rear wing on the required fuel mass. For a single aisle, medium range mission, a design with and… Advisors/Committee Members: Oliviero, Fabrizio (mentor), Delft University of Technology (degree granting institution).

Subjects/Keywords: Weight-Estimation; Closed-Wing; PrandtlPlane

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APA (6^th Edition):

Rousseau, R. (. (2017). Semi-Analytical Closed-Wing Weight Estimation during Conceptual Design. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:948ab573-cea8-43a7-af94-40a38994016b

Chicago Manual of Style (16^th Edition):

Rousseau, Rob (author). “Semi-Analytical Closed-Wing Weight Estimation during Conceptual Design.” 2017. Masters Thesis, Delft University of Technology. Accessed January 25, 2021. http://resolver.tudelft.nl/uuid:948ab573-cea8-43a7-af94-40a38994016b.

MLA Handbook (7^th Edition):

Rousseau, Rob (author). “Semi-Analytical Closed-Wing Weight Estimation during Conceptual Design.” 2017. Web. 25 Jan 2021.

Vancouver:

Rousseau R(. Semi-Analytical Closed-Wing Weight Estimation during Conceptual Design. [Internet] [Masters thesis]. Delft University of Technology; 2017. [cited 2021 Jan 25]. Available from: http://resolver.tudelft.nl/uuid:948ab573-cea8-43a7-af94-40a38994016b.

Council of Science Editors:

Rousseau R(. Semi-Analytical Closed-Wing Weight Estimation during Conceptual Design. [Masters Thesis]. Delft University of Technology; 2017. Available from: http://resolver.tudelft.nl/uuid:948ab573-cea8-43a7-af94-40a38994016b

University of Melbourne

13. Brett, James Daniel. Numerical study of the flow over delta wings.

Degree: 2016, University of Melbourne

URL: http://hdl.handle.net/11343/92383

► Delta wing aircraft are becoming more commonplace due to the increasing numbers of unmanned aerial vehicles (UAV) which favour designs capable of producing large amounts… (more)

Subjects/Keywords: CFD; delta wing; UAV

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APA (6^th Edition):

Brett, J. D. (2016). Numerical study of the flow over delta wings. (Doctoral Dissertation). University of Melbourne. Retrieved from http://hdl.handle.net/11343/92383

Chicago Manual of Style (16^th Edition):

Brett, James Daniel. “Numerical study of the flow over delta wings.” 2016. Doctoral Dissertation, University of Melbourne. Accessed January 25, 2021. http://hdl.handle.net/11343/92383.

MLA Handbook (7^th Edition):

Brett, James Daniel. “Numerical study of the flow over delta wings.” 2016. Web. 25 Jan 2021.

Vancouver:

Brett JD. Numerical study of the flow over delta wings. [Internet] [Doctoral dissertation]. University of Melbourne; 2016. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/11343/92383.

Council of Science Editors:

Brett JD. Numerical study of the flow over delta wings. [Doctoral Dissertation]. University of Melbourne; 2016. Available from: http://hdl.handle.net/11343/92383

Virginia Tech

14. Eger, Charles Alfred Gaitan. Design of a Scaled Flight Test Vehicle Including Linear Aeroelastic Effects.

Degree: MS, Aerospace Engineering, 2013, Virginia Tech

URL: http://hdl.handle.net/10919/23088

► A procedure for the design of a scaled aircraft using linear aeroelastic scaling is developed and demonstrated. Previous work has shown the viability in matching… (more)

Subjects/Keywords: Aeroelasticity; Scaling; Joined-wing

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APA (6^th Edition):

Eger, C. A. G. (2013). Design of a Scaled Flight Test Vehicle Including Linear Aeroelastic Effects. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/23088

Chicago Manual of Style (16^th Edition):

Eger, Charles Alfred Gaitan. “Design of a Scaled Flight Test Vehicle Including Linear Aeroelastic Effects.” 2013. Masters Thesis, Virginia Tech. Accessed January 25, 2021. http://hdl.handle.net/10919/23088.

MLA Handbook (7^th Edition):

Eger, Charles Alfred Gaitan. “Design of a Scaled Flight Test Vehicle Including Linear Aeroelastic Effects.” 2013. Web. 25 Jan 2021.

Vancouver:

Eger CAG. Design of a Scaled Flight Test Vehicle Including Linear Aeroelastic Effects. [Internet] [Masters thesis]. Virginia Tech; 2013. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/10919/23088.

Council of Science Editors:

Eger CAG. Design of a Scaled Flight Test Vehicle Including Linear Aeroelastic Effects. [Masters Thesis]. Virginia Tech; 2013. Available from: http://hdl.handle.net/10919/23088

University of New South Wales

15. Liu, Zhengliang. Numerical analysis of the performance of flapping foil power generators.

Degree: Aerospace, Civil & Mechanical Engineering, 2018, University of New South Wales

URL: http://handle.unsw.edu.au/1959.4/60105 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:51387/SOURCE02?view=true

► An innovative concept of wind turbines, the flapping foil power generator that exploits dynamic stall, is numerically studied at Reynolds number of 1100. The combination… (more)

▼ An innovative concept of wind turbines, the flapping foil power generator that exploits dynamic stall, is numerically studied at Reynolds number of 1100. The combination of the kinematic parameters and the coupling between the foil deformation and aerodynamic loads are investigated to uncover the physical mechanism for high performance.Firstly, the discrete vortex method (DVM) is improved to capture flow separations at the leading and trailing edges of the foil. Its results compare well with those of immersed boundary-lattice Boltzmann method (IB-LBM) and experiments. Its computational cost is at least two orders of magnitude less than that of the IB-LBM.Then, kinematic parameters are optimized using a multi-fidelity evolutionary algorithm implemented with a dynamic stall model and the improved DVM. The results show that despite the use of low fidelity models and limited budget of computational resources, the multi-fidelity strategy is capable of finding kinematic conditions suitable for high performance. In addition, detailed flow analysis using IB-LBM has revealed that high efficiency and power output are associated with the detachment of the leading edge vortex (LEV) near stroke reversal, resulting in a horseshoe-shaped vorticity wake with a width approximating the swept distance of foil behind the turbine plane. When the LEV detaches from the foil near mid stroke, both efficiency and power output suffer.Finally, a flexible system consisting of a rigid foil and a passively actuated flat plate tail connected through a torsional spring to the trailing edge of the rigid foil is studied numerically using the IB-LBM for different mass densities and natural frequencies under different kinematic conditions. The results show that a tail with appropriate mass density and resonant frequency can improve the maximum efficiency by 7.24% compared to the rigid system. This is because the deflection of the tail reduces the low pressure region on the pressure surface caused by the LEV after the stroke reversal, resulting in a higher efficiency. In addition, a spring-connected tail with a low resonant frequency improves the performance significantly at high flapping frequencies. Advisors/Committee Members: Tian, Fang-Bao, Aerospace, Civil & Mechanical Engineering, UNSW Canberra, UNSW, Young, John, Aerospace, Civil & Mechanical Engineering, UNSW Canberra, UNSW, Lai, Joseph, Aerospace, Civil & Mechanical Engineering, UNSW Canberra, UNSW.

Subjects/Keywords: Flapping wing; Power generator

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APA (6^th Edition):

Liu, Z. (2018). Numerical analysis of the performance of flapping foil power generators. (Doctoral Dissertation). University of New South Wales. Retrieved from http://handle.unsw.edu.au/1959.4/60105 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:51387/SOURCE02?view=true

Chicago Manual of Style (16^th Edition):

Liu, Zhengliang. “Numerical analysis of the performance of flapping foil power generators.” 2018. Doctoral Dissertation, University of New South Wales. Accessed January 25, 2021. http://handle.unsw.edu.au/1959.4/60105 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:51387/SOURCE02?view=true.

MLA Handbook (7^th Edition):

Liu, Zhengliang. “Numerical analysis of the performance of flapping foil power generators.” 2018. Web. 25 Jan 2021.

Vancouver:

Liu Z. Numerical analysis of the performance of flapping foil power generators. [Internet] [Doctoral dissertation]. University of New South Wales; 2018. [cited 2021 Jan 25]. Available from: http://handle.unsw.edu.au/1959.4/60105 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:51387/SOURCE02?view=true.

Council of Science Editors:

Liu Z. Numerical analysis of the performance of flapping foil power generators. [Doctoral Dissertation]. University of New South Wales; 2018. Available from: http://handle.unsw.edu.au/1959.4/60105 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:51387/SOURCE02?view=true

Utah State University

16. Goates, Joshua Taylor. Development of an Improved Low-Order Model for Propeller-Wing Interactions.

Degree: MS, Mechanical and Aerospace Engineering, 2018, Utah State University

URL: https://digitalcommons.usu.edu/etd/7394

► For aircraft that have propellers mounted in front of the wings or tail, the prop wash produced by the propellers can have a strong… (more)

Subjects/Keywords: Propeller; Wing; Aerodynamics; Mechanical Engineering

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APA (6^th Edition):

Goates, J. T. (2018). Development of an Improved Low-Order Model for Propeller-Wing Interactions. (Masters Thesis). Utah State University. Retrieved from https://digitalcommons.usu.edu/etd/7394

Chicago Manual of Style (16^th Edition):

Goates, Joshua Taylor. “Development of an Improved Low-Order Model for Propeller-Wing Interactions.” 2018. Masters Thesis, Utah State University. Accessed January 25, 2021. https://digitalcommons.usu.edu/etd/7394.

MLA Handbook (7^th Edition):

Goates, Joshua Taylor. “Development of an Improved Low-Order Model for Propeller-Wing Interactions.” 2018. Web. 25 Jan 2021.

Vancouver:

Goates JT. Development of an Improved Low-Order Model for Propeller-Wing Interactions. [Internet] [Masters thesis]. Utah State University; 2018. [cited 2021 Jan 25]. Available from: https://digitalcommons.usu.edu/etd/7394.

Council of Science Editors:

Goates JT. Development of an Improved Low-Order Model for Propeller-Wing Interactions. [Masters Thesis]. Utah State University; 2018. Available from: https://digitalcommons.usu.edu/etd/7394

University of Vermont

17. Fitz, William Peter. Reactionary Postmodernism? Neoliberalism, Multiculturalism, the Internet, and the Ideology of the New Far Right in Germany.

Degree: European Studies, 2018, University of Vermont

URL: https://scholarworks.uvm.edu/hcoltheses/275

► This thesis aims to map the material, discursive, and ideological foundations of the new far right in Germany within the context of neoliberalism and… (more)

Subjects/Keywords: Right wing extremism; right wing radicalism; Identity Politics; Memes; Postmodernity; Fascism

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APA (6^th Edition):

Fitz, W. P. (2018). Reactionary Postmodernism? Neoliberalism, Multiculturalism, the Internet, and the Ideology of the New Far Right in Germany. (Thesis). University of Vermont. Retrieved from https://scholarworks.uvm.edu/hcoltheses/275

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):

Fitz, William Peter. “Reactionary Postmodernism? Neoliberalism, Multiculturalism, the Internet, and the Ideology of the New Far Right in Germany.” 2018. Thesis, University of Vermont. Accessed January 25, 2021. https://scholarworks.uvm.edu/hcoltheses/275.

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

MLA Handbook (7^th Edition):

Fitz, William Peter. “Reactionary Postmodernism? Neoliberalism, Multiculturalism, the Internet, and the Ideology of the New Far Right in Germany.” 2018. Web. 25 Jan 2021.

Vancouver:

Fitz WP. Reactionary Postmodernism? Neoliberalism, Multiculturalism, the Internet, and the Ideology of the New Far Right in Germany. [Internet] [Thesis]. University of Vermont; 2018. [cited 2021 Jan 25]. Available from: https://scholarworks.uvm.edu/hcoltheses/275.

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

Council of Science Editors:

Fitz WP. Reactionary Postmodernism? Neoliberalism, Multiculturalism, the Internet, and the Ideology of the New Far Right in Germany. [Thesis]. University of Vermont; 2018. Available from: https://scholarworks.uvm.edu/hcoltheses/275

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

Universidade Nova

18. Ponte, Susana Isabel Pereira da. The role of Grainy head in epithelial tissue growth.

Degree: 2014, Universidade Nova

URL: http://www.rcaap.pt/detail.jsp?id=oai:run.unl.pt:10362/13839

►

Part of the results of this thesis was presented in the following meetings: Susana Ponte, Lara Carvalho, Inês Cristo and António Jacinto. The role of… (more)

▼

Part of the results of this thesis was presented in the following meetings: Susana Ponte, Lara Carvalho, Inês Cristo and António Jacinto. The role of Grainy head in epithelial tissue growth. Drostuga 2013. Faro, Portugal, January 3rd 2014 [poster] Susana Ponte, Lara Carvalho, Inês Cristo and António Jacinto. The role of Grainy head in epithelial tissue growth. Drostuga 2014. Tomar, Portugal, September 5th-6th 2014 [poster]

The grainy head (grh) gene family encodes an important group of transcription factors that play a remarkably conserved role in epithelial organ development, epithelial barrier formation and epithelial repair upon damage in different organisms. The regulation and molecular targets of Grh are numerous and seem to highly depend on the studied developmental context and tissue. Notably, the grh vertebrate homologs, called grh-like (grhl) genes, have recently been implicated in the pathogenesis of several human diseases, including tumor progression and metastasis in different types of cancer. However, the molecular mechanisms by which Grh exerts its function remain largely unknown. The main goal of this project was to investigate the role of Grh in epithelial growth and maintenance using the Drosophila melanogaster (fruit-fly) wing as an in vivo model system. We wanted to understand how Grh influences cell proliferation and apoptosis, as well as cell polarity, cell adhesion and cytoskeleton. Our results show that Grh is essential for epithelial cell survival, since both grh knockdown and overexpression lead to apoptosis. In addition, while grh knockdown induces an increase in cell proliferation, grh overexpression leads to the opposite phenotype, leading us to propose that this gene has a role in the control of cell proliferation. Grh seems to regulate both the expression and the localization of the cell adhesion protein E-cadherin in the wing disc epithelium. We also observed increased F-actin levels upon grh knockdown, suggesting that Grh can influence actin expression or dynamics. In conclusion, our data suggest that Grh is a key transcription factor in the regulation of epithelial maintenance and integrity of the Drosophila wing imaginal disc.

Advisors/Committee Members: Carvalho, Lara.

Subjects/Keywords: Grainy head; Epithelia; Growth; Drosophila; Wing; Wing imaginal disc

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APA (6^th Edition):

Ponte, S. I. P. d. (2014). The role of Grainy head in epithelial tissue growth. (Thesis). Universidade Nova. Retrieved from http://www.rcaap.pt/detail.jsp?id=oai:run.unl.pt:10362/13839

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):

Ponte, Susana Isabel Pereira da. “The role of Grainy head in epithelial tissue growth.” 2014. Thesis, Universidade Nova. Accessed January 25, 2021. http://www.rcaap.pt/detail.jsp?id=oai:run.unl.pt:10362/13839.

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

MLA Handbook (7^th Edition):

Ponte, Susana Isabel Pereira da. “The role of Grainy head in epithelial tissue growth.” 2014. Web. 25 Jan 2021.

Vancouver:

Ponte SIPd. The role of Grainy head in epithelial tissue growth. [Internet] [Thesis]. Universidade Nova; 2014. [cited 2021 Jan 25]. Available from: http://www.rcaap.pt/detail.jsp?id=oai:run.unl.pt:10362/13839.

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

Council of Science Editors:

Ponte SIPd. The role of Grainy head in epithelial tissue growth. [Thesis]. Universidade Nova; 2014. Available from: http://www.rcaap.pt/detail.jsp?id=oai:run.unl.pt:10362/13839

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

University of Vienna

19. Eder, Alexander. Motive im Wing Chun.

Degree: 2017, University of Vienna

URL: http://othes.univie.ac.at/46752/

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Wing Chun ist eine Kampfkunst, die sich in die Sparte des chinesischen Kung Fu einreiht. Ihre Entstehungsgeschichte ist verworren und von Uneinigkeiten geprägt. Es handelt… (more)

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Wing Chun ist eine Kampfkunst, die sich in die Sparte des chinesischen Kung Fu einreiht. Ihre Entstehungsgeschichte ist verworren und von Uneinigkeiten geprägt. Es handelt sich dabei um eine sehr technische, komplexe Kampfkunst, die hohen Stellenwert auf Effektivität legt und somit einen starken Selbstverteidigungscharakter aufweist. In der westlichen Welt ist Wing Chun vor allem durch Ip Man und seinen Schüler Bruce Lee bekannt geworden, der, unter anderem, durch seine Filmerfolge viele Menschen dazu motivierte, eine Kampfkunst zu erlernen. Neben Bruce Lee gibt es jedoch auch andere Beweggründe Kampfkunst zu betreiben. Die vorliegende Arbeit versucht weitere Motive, die der Ausübung von Wing Chun zu Grunde liegen, aufzuzeigen und zu erklären. Dazu wurde ein Online-Fragebogen erstellt, der auf das Berner Motiv- und Zielinventar von Lehnert, Sudeck und Conzelmann aufbaut, und an Wing Chun Praktizierende aus ganz Österreich verteilt. Einhundertsechsundvierzig vollständig ausgefüllte Fragebögen wurden im nächsten Schritt mit dem Statistikprogramm SPSS ausgewertet. Die für die Ausübung von Wing Chun bedeutsamsten Motive sind die „Motorische Verbesserung“ und die „Psychomotorische Verbesserung“, gefolgt von „Fitness/Gesundheit“. Auch der Selbstverteidigungsaspekt spielt eine wichtige Rolle, steht jedoch weder bei Frauen, noch bei Männern im Vordergrund. Am unbedeutendsten als Beweggrund sind die Motivfaktoren „Wettkampf/Leistung“ und „Figur/Aussehen“. Zusammenfassend lässt sich sagen, dass die Motive Wing Chun Praktizierender vielseitig geprägt sind und es signifikante Zusammenhänge und Unterschiede zwischen verschiedenen Merkmalsausprägungen bezüglich den Motiven im Wing Chun gibt. So gewichten, zum Beispiel, Männer die Motivfaktoren „Wettkampf/Leistung“, „Fitness/Gesundheit“ und „Positive Erschöpfung“ höher als Frauen. Wing Chun Praktizierende, die zusätzlich mindestens eine weitere Kampfkunst/-kampfsportart ausüben, bewerten die Motivatoren „Motorische Verbesserung“ und „Wettkampf/Leistung“ höher, den Beweggrund „Figur/Aussehen“ jedoch niedriger als jene, die nur Wing Chun praktizieren. Mit zumehmendem Alter der Teilnehmer/innen sinkt die Bedeutung der Faktoren „Selbstverteidigung/Selbstbewusstsein“ und „Vorbild“, während die Wichtigkeit des Motivs „Ästhetik“ steigt.

Wing Chun is a martial art belonging to the category of Chinese Kung Fu. Its history is tangled and marked by dissension. It is a rather technical, complex martial art that stresses effectiveness and is therefore strongly associated with self-defense. In the western world it is mainly known through Ip Man and his disciple Bruce Lee, who, amongst other things, motivated people to study martial arts through his films. However, Bruce Lee is not the only reason to dedicate oneself to studying martial arts. The present work aims to explore and explain motives precipitating the practice of Wing Chun. To that end an online survey, based on the Berner Motiv- und Zielinventar from Lehnert, Sudeck und Conzelmann, was created, and distributed to Wing Chun…

Subjects/Keywords: 76.11 Sportsoziologie, Sportpsychologie; Wing Chun / Motive; Wing Chun / motives

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

APA (6^th Edition):

Eder, A. (2017). Motive im Wing Chun. (Thesis). University of Vienna. Retrieved from http://othes.univie.ac.at/46752/

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):

Eder, Alexander. “Motive im Wing Chun.” 2017. Thesis, University of Vienna. Accessed January 25, 2021. http://othes.univie.ac.at/46752/.

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

MLA Handbook (7^th Edition):

Eder, Alexander. “Motive im Wing Chun.” 2017. Web. 25 Jan 2021.

Vancouver:

Eder A. Motive im Wing Chun. [Internet] [Thesis]. University of Vienna; 2017. [cited 2021 Jan 25]. Available from: http://othes.univie.ac.at/46752/.

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

Council of Science Editors:

Eder A. Motive im Wing Chun. [Thesis]. University of Vienna; 2017. Available from: http://othes.univie.ac.at/46752/

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

Univerzitet u Beogradu

20. Đorić, Marija R., 1981-. Идеолошки мотивисан екстремизам као генератор политичкиг насиља.

Degree: Fakultet političkih nauka, 2015, Univerzitet u Beogradu

URL: https://fedorabg.bg.ac.rs/fedora/get/o:7253/bdef:Content/get

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Политичке науке / Political sciences

У раду се истражује које све то облике политичког насиља може генерисати идеолошки мотивисан екстремизам и под којим условима. Како… (more)

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Политичке науке / Political sciences

У раду се истражује које све то облике политичког насиља може генерисати идеолошки мотивисан екстремизам и под којим условима. Како је екстремизам релативно аморфан и поприлично варијабилан феномен пре свега због сличности са осталим феноменима попут тероризма, фанатизма, фундаментализма и популизма, али и због временске, просторне и културолошке условљености, направили смо његову класификацију на основу различитих критеријума. Сматрали смо да је најпоузданије извршити класификацију екстремизма на основу програмско-циљне оријентације, његових актера, метода и средстава, као и времена настанка. Узимајући у обзир да је идеологија један од “најнеухватљивијих феномена” у друштвеним наукама са при том изузетно великим утицајем на политичка дешавања, одлучили смо се да испитамо које све то идеолошке опције утичу на профилисање левичарског и десничарског екстремизма. Иако постоји низ разлика међу њима, екстремна левица и екстремна десница су веома сродне по следећим карактеристикама: негирају демократију и њене инструменте попут толеранције, парламентаризма и легализма и оно што је најопасније – примењују насиље као метод деловања. Док социјализам, анархизам, екологизам и феминизам представљају идеолошку базу која предодређује екстремну левицу, фашизам, национализам, религијски фундаментализам и конзервативизам могу представљати идеолошку основу из које ће се развити екстремна десница. Утврђено је да се већина основних и сложених облика политичког насиља може изродити под утицајем идеолошки фундираног екстремизма. Неки облици насиља су типични за екстремну левицу, попут револуције и гериле, и ретко се могу наћи код екстремних десничара. Испитиван је и каузални однос између идеолошки мотивисаног екстремизма и глобализације због њихових дијаметрално супротних вредносних система, али и њихове међусобне условљености у одређеним сферама. Утврђено је да денационализација, десуверенизација и универзализација које пропагира глобализација подстрекују екстремне десничаре на насилно деловање, док се екстремни левичари боре против експлоатације сиромашних и великих економских разлика које производи глобализација.Да би се што боље схватиле специфичности савременог идеолошки мотивисаног екстремизма направљена је компаративна анализа најзначајнијих актера која је обухватила подручје САД, Европе и Србије. Када је реч о екстремној десници она је у САД поникла на принципима расизма који су дубоко утемељени у њену традицију (још од времена настанка Кју Клукс Клана). У Европи десничарски екстремизам настаје као одговор на прилив великог броја имиграната који рађају ксенофобију, док је у Србији екстремна десница производ национализма који је био главни подстрекач грађанских ратова на просторима бивше СФРЈ 90-их година 20. века. Левичарски екстремизам се интензивира захваљујући светској економској кризи која је “пробудила” многе анархистичке организације. Осим анархизма, екстремна левица је генерисала и еко-екстремизам који је актуелан пре свега на просторима САД и Велике Британије. У европским земљама се…

Advisors/Committee Members: Simeunović, Dragan, 1953-.

Subjects/Keywords: extremism; ideology; left wing; right wing; terrorism; political violence

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

APA (6^th Edition):

Đorić, Marija R., 1. (2015). Идеолошки мотивисан екстремизам као генератор политичкиг насиља. (Thesis). Univerzitet u Beogradu. Retrieved from https://fedorabg.bg.ac.rs/fedora/get/o:7253/bdef:Content/get

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):

Đorić, Marija R., 1981-. “Идеолошки мотивисан екстремизам као генератор политичкиг насиља.” 2015. Thesis, Univerzitet u Beogradu. Accessed January 25, 2021. https://fedorabg.bg.ac.rs/fedora/get/o:7253/bdef:Content/get.

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

MLA Handbook (7^th Edition):

Đorić, Marija R., 1981-. “Идеолошки мотивисан екстремизам као генератор политичкиг насиља.” 2015. Web. 25 Jan 2021.

Vancouver:

Đorić, Marija R. 1. Идеолошки мотивисан екстремизам као генератор политичкиг насиља. [Internet] [Thesis]. Univerzitet u Beogradu; 2015. [cited 2021 Jan 25]. Available from: https://fedorabg.bg.ac.rs/fedora/get/o:7253/bdef:Content/get.

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

Council of Science Editors:

Đorić, Marija R. 1. Идеолошки мотивисан екстремизам као генератор политичкиг насиља. [Thesis]. Univerzitet u Beogradu; 2015. Available from: https://fedorabg.bg.ac.rs/fedora/get/o:7253/bdef:Content/get

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

Delft University of Technology

21. Epema, Kitso (author). Wing Optimisation for Tractor Propeller Configurations: Validation and Application of Low-Order Numerical Models Adapted to Include Propeller-Induced Velocities.

Degree: 2017, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:b091880e-7a0a-423c-a11e-6afe9b9575e3

► Even though propellers are the oldest form of propulsion, they are still a popular choice for unmanned aerial vehicles (UAVs) and passenger aircraft in certain… (more)

▼ Even though propellers are the oldest form of propulsion, they are still a popular choice for unmanned aerial vehicles (UAVs) and passenger aircraft in certain market segments. If the propellers are mounted on the wing, strong propeller-wing interactions alter the aerodynamic efficiency of the aircraft. Using low-order numerical models, it is shown in literature that the wing chord and twist distribution can be changed to maximise this efficiency. These results are only theoretical. This thesis, therefore, aims to validate and apply a numerical model for optimisation of the wing design taking propeller-wing interactions into account. A vortex lattice method (VLM) was adapted to include the effects of propeller-induced velocities. Comparing the results of the adapted VLM with existing experimental data already validates the numerical model for predicting the lift distribution. To validate it for changes in lift distribution due to wing design changes, a wind-tunnel experiment is set up. Two wings are tested in a tractor propeller configuration. The only difference between the wings is in the twist distribution. To find the lift distribution, the circulation is evaluated in the flow around a wing at several stations along the wingspan. Particle-image velocimetry was used to obtain this flow field. Indeed, the lift distributions measured on both wings are matched by predictions from the adapted VLM, which proofs the numerical model is suitable for qualitative optimisation studies. For the wing and operating conditions used for the wind-tunnel experiment, an optimisation study is performed using the adapted VLM. It shows the drag can be reduced with 34% by adopting the optimal chord and twist distribution. Even though the operating conditions are not representative for full-scale aircraft or UAVs, it does show there is a great potential for taking propeller-wing interactions into account for the design of the wing. Advisors/Committee Members: Sinnige, Tomas (mentor), Veldhuis, Leo (graduation committee), Vos, Roelof (graduation committee), Sciacchitano, Andrea (graduation committee), Delft University of Technology (degree granting institution).

Subjects/Keywords: propeller-wing interaction; optimisation; vortex lattice method; lifting line; propeller; wing

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APA (6^th Edition):

Epema, K. (. (2017). Wing Optimisation for Tractor Propeller Configurations: Validation and Application of Low-Order Numerical Models Adapted to Include Propeller-Induced Velocities. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:b091880e-7a0a-423c-a11e-6afe9b9575e3

Chicago Manual of Style (16^th Edition):

Epema, Kitso (author). “Wing Optimisation for Tractor Propeller Configurations: Validation and Application of Low-Order Numerical Models Adapted to Include Propeller-Induced Velocities.” 2017. Masters Thesis, Delft University of Technology. Accessed January 25, 2021. http://resolver.tudelft.nl/uuid:b091880e-7a0a-423c-a11e-6afe9b9575e3.

MLA Handbook (7^th Edition):

Epema, Kitso (author). “Wing Optimisation for Tractor Propeller Configurations: Validation and Application of Low-Order Numerical Models Adapted to Include Propeller-Induced Velocities.” 2017. Web. 25 Jan 2021.

Vancouver:

Epema K(. Wing Optimisation for Tractor Propeller Configurations: Validation and Application of Low-Order Numerical Models Adapted to Include Propeller-Induced Velocities. [Internet] [Masters thesis]. Delft University of Technology; 2017. [cited 2021 Jan 25]. Available from: http://resolver.tudelft.nl/uuid:b091880e-7a0a-423c-a11e-6afe9b9575e3.

Council of Science Editors:

Epema K(. Wing Optimisation for Tractor Propeller Configurations: Validation and Application of Low-Order Numerical Models Adapted to Include Propeller-Induced Velocities. [Masters Thesis]. Delft University of Technology; 2017. Available from: http://resolver.tudelft.nl/uuid:b091880e-7a0a-423c-a11e-6afe9b9575e3

Delft University of Technology

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

Degree: 2015, Delft University of Technology

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

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

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

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

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

APA (6^th Edition):

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

Chicago Manual of Style (16^th Edition):

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

MLA Handbook (7^th Edition):

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

Vancouver:

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

Council of Science Editors:

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

University of Helsinki

23. Pullinen, Leena. Impressions of left-wing and right-wing values, and differences in impressions of left-wing and right-wing values between left-wingers and right-wingers in Finland: Suomalaisten mielikuvat vasemmiston ja oikeiston arvoista sekä erot vasemmistolaisten ja oikeistolaisten mielikuvien välillä.

Degree: Institute of Behavioural Sciences; Helsingfors universitet, Beteendevetenskapliga fakulteten, Institutionen för beteendevetenskaper, 2014, University of Helsinki

URL: http://hdl.handle.net/10138/154861

► Tavoitteet. Vasemmisto ja oikeisto ovat politiikassa laajalti käytettyjä termejä. Niillä ei ole tarkkoja akateemisia määritelmiä, mutta oikeisto on usein liitetty konservatiivisuuteen ja autoritaarisuuteen, ja vasemmisto… (more)

▼ Tavoitteet. Vasemmisto ja oikeisto ovat politiikassa laajalti käytettyjä termejä. Niillä ei ole tarkkoja akateemisia määritelmiä, mutta oikeisto on usein liitetty konservatiivisuuteen ja autoritaarisuuteen, ja vasemmisto liberaalisuuteen ja tasa-arvoon. Arvot ovat periaatteita, joita käytetään tekojen valintaan sekä ihmisten ja tilanteiden arviointiin. Schwartzin 10 perusarvoa ovat universalismi, hyväntahtoisuus, perinteet, yhdenmukaisuus, turvallisuus, valta, suoriutuminen, mielihyvä, virikkeisyys ja itseohjautuvuus. Ne voidaan ilmaista kahdella arvoulottuvuudella: itsen ylittäminen vs. itsekorostus ja konservatiivisuus vs. avoimuus muutokselle. Vasemmistolaisuus on yhdistetty itsen ylittämiseen ja avoimuuteen muutokselle, oikeistolaisuus itsen korostamiseen ja konservatiivisuuteen Länsi-Euroopassa, myös Suomessa. Tutkielman tavoitteena oli selvittää suomalaisten mielikuvia vasemmiston ja oikeiston arvoista sekä mielikuvien eroja oikeistolaisten ja vasemmistolaisten välillä käyttäen Schwartzin arvoja ja arvoulottuvuuksia. Menetelmät. Aineisto kerättiin v. 2012 Internet-kyselyllä. Osanottajat (N=1886) rekrytoitiin sähköpostilistojen kautta. Heitä pyydettiin kertomaan oma sijaintinsa vasen-oikea-jatkumolla (0=vasen, 10=oikea). Arvoja sekä mielikuvia vasemmiston ja oikeiston arvoista mitattiin Short Schwartz Values Survey –kyselyllä (SSVS). Keskiarvoja vertailtiin t-testeillä sen selvittämiseksi, nähtiinkö kukin arvo enemmän vasemmistolaisena kuin oikeistolaisena tai päinvastoin. Arvohierarkioiden avulla tarkasteltiin arvojen suhteellisia tärkeysjärjestyksiä. Tulokset ja johtopäätökset. Universalismi ja hyväntahtoisuus nähtiin enemmän vasemmistolaisina kuin oikeistolaisina. Kaikkia muita arvoja pidettiin enemmän oikeistolaisina kuin vasemmistolaisina. Oikeistolaiset nähtiin konservatiivisempina ja vasemmistolaiset enemmän itseään ylittävinä. Vasemmistolaisten ja oikeistolaisten mielikuvat vasemmistolaisista ja oikeistolaisista arvoista kuitenkin erosivat toisistaan tavalla, joka saattaa viitata sisäryhmä-ulkoryhmä-vinoumaan. Kumpikin ryhmä uskoi, että toinen ryhmä arvostaa eniten valtaa ja toisaalta mielihyvää enemmän kuin oma sisäryhmä. Vasemmistolaiset uskoivat oikeistolaisten arvostavan hyväntahtoisuutta ja universalismia sisäryhmää vähemmän. Tulokset auttavat ymmärtämään, mitä ihmiset tarkoittavat poliittisen oikean ja vasemman käsitteillä. Ne myös auttamat selittämään, miksi poliittinen keskustelu polarisoituu helposti.

Subjects/Keywords: left-wing; right-wing; values; impressions; Psychology; Psykologia; Psykologi

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

APA (6^th Edition):

Pullinen, L. (2014). Impressions of left-wing and right-wing values, and differences in impressions of left-wing and right-wing values between left-wingers and right-wingers in Finland: Suomalaisten mielikuvat vasemmiston ja oikeiston arvoista sekä erot vasemmistolaisten ja oikeistolaisten mielikuvien välillä. (Masters Thesis). University of Helsinki. Retrieved from http://hdl.handle.net/10138/154861

Chicago Manual of Style (16^th Edition):

Pullinen, Leena. “Impressions of left-wing and right-wing values, and differences in impressions of left-wing and right-wing values between left-wingers and right-wingers in Finland: Suomalaisten mielikuvat vasemmiston ja oikeiston arvoista sekä erot vasemmistolaisten ja oikeistolaisten mielikuvien välillä.” 2014. Masters Thesis, University of Helsinki. Accessed January 25, 2021. http://hdl.handle.net/10138/154861.

MLA Handbook (7^th Edition):

Pullinen, Leena. “Impressions of left-wing and right-wing values, and differences in impressions of left-wing and right-wing values between left-wingers and right-wingers in Finland: Suomalaisten mielikuvat vasemmiston ja oikeiston arvoista sekä erot vasemmistolaisten ja oikeistolaisten mielikuvien välillä.” 2014. Web. 25 Jan 2021.

Vancouver:

Pullinen L. Impressions of left-wing and right-wing values, and differences in impressions of left-wing and right-wing values between left-wingers and right-wingers in Finland: Suomalaisten mielikuvat vasemmiston ja oikeiston arvoista sekä erot vasemmistolaisten ja oikeistolaisten mielikuvien välillä. [Internet] [Masters thesis]. University of Helsinki; 2014. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/10138/154861.

Council of Science Editors:

Pullinen L. Impressions of left-wing and right-wing values, and differences in impressions of left-wing and right-wing values between left-wingers and right-wingers in Finland: Suomalaisten mielikuvat vasemmiston ja oikeiston arvoista sekä erot vasemmistolaisten ja oikeistolaisten mielikuvien välillä. [Masters Thesis]. University of Helsinki; 2014. Available from: http://hdl.handle.net/10138/154861

University of Louisville

24. Broering, Timothy Michael, 1985-. The characterization of wing-wing vortex interactions of a tandem flapping wing configuration and its relationship to the phase angle and wing spacing.

Degree: PhD, 2013, University of Louisville

URL: 10.18297/etd/157 ; https://ir.library.louisville.edu/etd/157

► A number of flying insects make use of tandem wing configurations, suggesting that such a setup may have potential advantages over a single wing at… (more)

▼ A number of flying insects make use of tandem wing configurations, suggesting that such a setup may have potential advantages over a single wing at low Reynolds numbers. Dragonflies, which are fast and highly maneuverable, demonstrate well, the potential performance of such a configuration. In a tandem wing configuration, the hindwing often operates in the wake of the forewing and, hence, its performance is affected by the vortices shed by the forewing. Changes in the phase angle between the flapping motions of the fore and hind wings, as well as the spacing between them, can affect the resulting vortex/wing and vortex/vortex interactions. In this thesis flapping wings in a tandem configuration were simulated using an incompressible Navier-Stokes solver on composite overlapping grids. Harmonic single frequency sinusoidal oscillations consisting of combined pitch and plunge motions were used for the flapping wing kinematics at a Strouhal number of 0.3. Different wing spacings ranging from 0.1 chords to 1 chord were tested at three different phase angles, 0°, 90° and 180°. It was found that changes in the spacing and phase angle affected the timing of the interaction between the vortex shed from the forewing and the hindwing. Such an interaction affects the LEV formation on the hindwing and results in changes to the aerodynamic force production and efficiencies of the hindwing. It is also observed that changing the phase angle has a similar effect as changing the spacing. The results further show that at different spacings the peak force generation occurs at different phase angles, as do the peak efficiencies. The aerodynamics of the hindwing was also compared in detail to a single wing, with the same geometry and undergoing the same flapping kinematics, to determine the effect of vortex shedding from the forewing on the hindwing, as well as how the phase angle affects the interaction. The average lift, thrust and power coefficients and the average efficiency of the fore and hind wings were compared to a single wing to determine how the tandem wing interaction affects performance. Advisors/Committee Members: Lian, Yongsheng.

Subjects/Keywords: CFD; Tandem wing; Fluid dynamics; Dragonfly; Flapping wing; Aerospace engineering

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APA (6^th Edition):

Broering, Timothy Michael, 1. (2013). The characterization of wing-wing vortex interactions of a tandem flapping wing configuration and its relationship to the phase angle and wing spacing. (Doctoral Dissertation). University of Louisville. Retrieved from 10.18297/etd/157 ; https://ir.library.louisville.edu/etd/157

Chicago Manual of Style (16^th Edition):

Broering, Timothy Michael, 1985-. “The characterization of wing-wing vortex interactions of a tandem flapping wing configuration and its relationship to the phase angle and wing spacing.” 2013. Doctoral Dissertation, University of Louisville. Accessed January 25, 2021. 10.18297/etd/157 ; https://ir.library.louisville.edu/etd/157.

MLA Handbook (7^th Edition):

Broering, Timothy Michael, 1985-. “The characterization of wing-wing vortex interactions of a tandem flapping wing configuration and its relationship to the phase angle and wing spacing.” 2013. Web. 25 Jan 2021.

Vancouver:

Broering, Timothy Michael 1. The characterization of wing-wing vortex interactions of a tandem flapping wing configuration and its relationship to the phase angle and wing spacing. [Internet] [Doctoral dissertation]. University of Louisville; 2013. [cited 2021 Jan 25]. Available from: 10.18297/etd/157 ; https://ir.library.louisville.edu/etd/157.

Council of Science Editors:

Broering, Timothy Michael 1. The characterization of wing-wing vortex interactions of a tandem flapping wing configuration and its relationship to the phase angle and wing spacing. [Doctoral Dissertation]. University of Louisville; 2013. Available from: 10.18297/etd/157 ; https://ir.library.louisville.edu/etd/157

University of New South Wales

25. Shahzad, Aamer. Numerical analysis of the effects of flexibility, shapes and aspect ratios on hovering wing aerodynamics.

Degree: Engineering & Information Technology, 2018, University of New South Wales

URL: http://handle.unsw.edu.au/1959.4/60041 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:51369/SOURCE02?view=true

► Biological flight has inspired the development of micro aerial vehicles but the effects of flexibility, shapes and aspect ratios (AR) on hovering wing aerodynamics are… (more)

▼ Biological flight has inspired the development of micro aerial vehicles but the effects of flexibility, shapes and aspect ratios (AR) on hovering wing aerodynamics are still not fully understood. Here, the aerodynamic performance of a hovering wing with three shapes, defined by the radius of the first moment of wing area, r1 (= 0.43, 0.53 and 0.63), and four AR (= 1.5, 2.96, 4.5 and 6.0) has been studied numerically using a 3-D Navier-Stokes solver coupled with a structure solver. The performance trends of rigid wings at the Reynolds number (Re) of 12, 400 and 13500 have been observed to be independent of Re, because high suction pressures associated with the leading edge vortex are predominantly spread towards the tip and the trailing edge at all Re. Isotropic homogeneous flexible wings are modeled with a rigid leading edge at Re of 400. Although the lift is maximized using high (r1) and AR wings, low r1 and high AR (rigid and isotropic flexible wings at high mass ratio, m* = 4.0) are best for maximizing power economy (PE) for a given lift because small proportion of the wing area close to the distal region results in less aerodynamic power. However, at low m* = 0.66, there is a limited range of lift for which low r1 and high AR wings are efficient. Except for AR = 1.5, isotropic flexible wings have higher PE than rigid wings for all shapes. The effect of anisotropic flexibility on the performance is investigated by mapping the stiffness distribution of hawkmoth wing on all shapes at Re of 400. For a given shape, all anisotropic flexible wings generally produce more lift than rigid wings (except r1 = 0.53 and 0.63 at AR = 6.0) due to strong leading edge vortex resulting from combined chordwise-spanwise deformation, but not higher PE. Results here show that PE is maximized for hovering hawkmoth wings. Maximum PE for rigid, isotropic or anisotropic flexible wings is typically achieved at AR = 2.96, as low AR wing does not produce enough lift and high AR wings consume more aerodynamic power. Advisors/Committee Members: Lai, Joseph, Engineering & Information Technology, UNSW Canberra, UNSW, Tian, Fangbao, Engineering & Information Technology, UNSW Canberra, UNSW, Young, John, Engineering & Information Technology, UNSW Canberra, UNSW.

Subjects/Keywords: Aspect ratio; Flapping wing; Wing shape; Flexibility; Fluid-structure interaction

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APA (6^th Edition):

Shahzad, A. (2018). Numerical analysis of the effects of flexibility, shapes and aspect ratios on hovering wing aerodynamics. (Doctoral Dissertation). University of New South Wales. Retrieved from http://handle.unsw.edu.au/1959.4/60041 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:51369/SOURCE02?view=true

Chicago Manual of Style (16^th Edition):

Shahzad, Aamer. “Numerical analysis of the effects of flexibility, shapes and aspect ratios on hovering wing aerodynamics.” 2018. Doctoral Dissertation, University of New South Wales. Accessed January 25, 2021. http://handle.unsw.edu.au/1959.4/60041 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:51369/SOURCE02?view=true.

MLA Handbook (7^th Edition):

Shahzad, Aamer. “Numerical analysis of the effects of flexibility, shapes and aspect ratios on hovering wing aerodynamics.” 2018. Web. 25 Jan 2021.

Vancouver:

Shahzad A. Numerical analysis of the effects of flexibility, shapes and aspect ratios on hovering wing aerodynamics. [Internet] [Doctoral dissertation]. University of New South Wales; 2018. [cited 2021 Jan 25]. Available from: http://handle.unsw.edu.au/1959.4/60041 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:51369/SOURCE02?view=true.

Council of Science Editors:

Shahzad A. Numerical analysis of the effects of flexibility, shapes and aspect ratios on hovering wing aerodynamics. [Doctoral Dissertation]. University of New South Wales; 2018. Available from: http://handle.unsw.edu.au/1959.4/60041 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:51369/SOURCE02?view=true

The Ohio State University

26. Trussa, Colin Weidner. Low-Speed Aerodynamic Characteristics of a Delta Wing with Deflected Wing Tips.

Degree: MS, Aero/Astro Engineering, 2020, The Ohio State University

URL: http://rave.ohiolink.edu/etdc/view?acc_num=osu1586450691890636

► The purpose of this work was to investigate the low-speed aerodynamic characteristics of a novel delta wing layout with deflected wing tips. This project is… (more)

▼ The purpose of this work was to investigate the low-speed aerodynamic characteristics of a novel delta wing layout with deflected wing tips. This project is motivated by the ongoing unmanned aerial vehicle research and development at The Ohio State University Aerospace Research Center. The model under test for this study had four main design requirements: (1) high-speed, (2) highly maneuverable, (3) aerodynamically interesting, and (4) multi-configurable. The last three requirements are addressed directly in this report with specific emphasis on requirements two and three. A modular fuselage design satisfied requirement four, and the novel delta wing addressed requirements two and three.The novel delta wing has a leading-edge sweep of 60 degrees, a high-speed airfoil with a rounded leading-edge, and wing tips that can rotate a full 180 degrees about a hinge, located at 2/3rds of the half-span parallel to fuselage centerline. Three different wing tip deflection configurations were analyzed: positive, negative, and asymmetric. Positive wing tip deflection corresponds to the wing tips being deflected up towards the vertical tail. Negative wing tip deflection is when the wing tips are deflected down, away from the vertical tail. While the asymmetric configuration has one wing tip deflected up and the other down.Analysis on the model was completed using a panel method code and experimental wind tunnel testing. The panel method code used was OpenVSP. Upon implementing a vortex lift factor, it was determined that the delta wing results from OpenVSP were only useful for lift related data after comparing the panel method results to theory and publicly available delta wing data. The wind tunnel used for this work is located at the Aerospace Research Center. The wind tunnel is an open circuit subsonic wind tunnel with a 3’x5’ test section. Aerodynamic forces were measured using an internal six-component force balance. Tests were performed at two different Reynolds numbers, 3.65x105 and 5x105. Significant results from wind tunnel testing found that as the wing tip deflection is increased, for all three layouts, the static longitudinal stability of the model decreased with no significant loss in lift characteristics. The adjustable stability as a result of rotating a delta wing’s wing tips, provides inflight adjustments to the maneuverability characteristics of the aircraft. Advisors/Committee Members: Whitfield, Clifford (Advisor).

Subjects/Keywords: Aerospace Engineering; delta wing; deflected wing tips; low-speed aerodynamics

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

APA (6^th Edition):

Trussa, C. W. (2020). Low-Speed Aerodynamic Characteristics of a Delta Wing with Deflected Wing Tips. (Masters Thesis). The Ohio State University. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=osu1586450691890636

Chicago Manual of Style (16^th Edition):

Trussa, Colin Weidner. “Low-Speed Aerodynamic Characteristics of a Delta Wing with Deflected Wing Tips.” 2020. Masters Thesis, The Ohio State University. Accessed January 25, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=osu1586450691890636.

MLA Handbook (7^th Edition):

Trussa, Colin Weidner. “Low-Speed Aerodynamic Characteristics of a Delta Wing with Deflected Wing Tips.” 2020. Web. 25 Jan 2021.

Vancouver:

Trussa CW. Low-Speed Aerodynamic Characteristics of a Delta Wing with Deflected Wing Tips. [Internet] [Masters thesis]. The Ohio State University; 2020. [cited 2021 Jan 25]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1586450691890636.

Council of Science Editors:

Trussa CW. Low-Speed Aerodynamic Characteristics of a Delta Wing with Deflected Wing Tips. [Masters Thesis]. The Ohio State University; 2020. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1586450691890636

Indian Institute of Science

27. Mysa, Ravi Chaithanya. Fluid-Elastic Interactions in Flutter And Flapping Wing Propulsion.

Degree: PhD, Faculty of Engineering, 2017, Indian Institute of Science

URL: http://etd.iisc.ac.in/handle/2005/2706

► This study seeks to understand the interplay of vorticity and elasto-dynamics that forms the basis for a fluttering flag and flapping wing propulsion, and factors… (more)

▼ This study seeks to understand the interplay of vorticity and elasto-dynamics that forms the basis for a fluttering flag and flapping wing propulsion, and factors that distinguish one from the other. The fluid dynamics is assumed two dimensional and incompressible, and comprises potential and viscous flow simulations. The elastic solid is one dimensional and governed by the Bernoulli-Euler flexure model. The fluid and elastic solid models are coupled using a predictor-corrector algorithm. Flutter of a flag or foil is associated with drag and we show that the pressure on the foil is predominantly circulatory in origin. The circulatory pressure generated on the foil depends primarily on the slope and curvature. The wake vorticity exhibits a wide range of behavior starting from a Kelvin-Helmholtz type instability to a von Kármán wake. Potential flow simulations do not capture the wake accurately both at high and low mass ratios. This is reflected in the flutter boundary and pressure over the foil when compared with viscous flow simulations. Thrust due to heaving of a flexible foil shows maxima at a set of discrete frequencies that coincide with the frequencies at which the flapping velocity of the foil tip is a maximum. The propulsive efficiency shows maxima at a set of discrete frequencies that are close but distinct from the thrust maxima set of frequencies. These discrete frequencies are close to the natural frequencies of vibration of a cantilevered foil vibrating in vacuum. At low frequencies thrust is a consequence of a strong leading edge vortex developed over the foil and it remains attached to the foil as it is convected due to the favorable pressure gradient presented by the time and spatially varying shape of the foil. At moderate and high frequencies of oscillation the pressure, and consequently the thrust, generated by the foil is non-circulatory in origin and they are high where the accelerations of the foil are high. At high frequencies the leading edge vortex is weak. Except in the low frequency range, potential flow simulations qualitatively compares well with viscous flow predictions. We show that thrust and drag on a flexible foil oscillating in a flow is caused by the phase difference between the slope of the foil and the fluid pressure on it. Propulsive efficiency though is governed by the phase difference between foil velocity and fluid pressure and inertia forces. Thus, the interplay of vorticity and elasto-dynamics determine the behavior of a flutter and propulsion of a flexible foil in a fluid flow. Advisors/Committee Members: Venkatraman, Kartik (advisor).

Subjects/Keywords: Wing Propulsion; Flapping Wing Propulsion; Fluttering Wing Propulsion; Fluttering Flags; Flapping Foils; Wing Propulsion Vorticity; Wing Propulsion Elasto-Dynamics; Viscous Fluid Flow; Flexible Foil; Aerospace Engineering

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

APA (6^th Edition):

Mysa, R. C. (2017). Fluid-Elastic Interactions in Flutter And Flapping Wing Propulsion. (Doctoral Dissertation). Indian Institute of Science. Retrieved from http://etd.iisc.ac.in/handle/2005/2706

Chicago Manual of Style (16^th Edition):

Mysa, Ravi Chaithanya. “Fluid-Elastic Interactions in Flutter And Flapping Wing Propulsion.” 2017. Doctoral Dissertation, Indian Institute of Science. Accessed January 25, 2021. http://etd.iisc.ac.in/handle/2005/2706.

MLA Handbook (7^th Edition):

Mysa, Ravi Chaithanya. “Fluid-Elastic Interactions in Flutter And Flapping Wing Propulsion.” 2017. Web. 25 Jan 2021.

Vancouver:

Mysa RC. Fluid-Elastic Interactions in Flutter And Flapping Wing Propulsion. [Internet] [Doctoral dissertation]. Indian Institute of Science; 2017. [cited 2021 Jan 25]. Available from: http://etd.iisc.ac.in/handle/2005/2706.

Council of Science Editors:

Mysa RC. Fluid-Elastic Interactions in Flutter And Flapping Wing Propulsion. [Doctoral Dissertation]. Indian Institute of Science; 2017. Available from: http://etd.iisc.ac.in/handle/2005/2706

Grand Valley State University

28. Durrer, Simon. Aerodynamics of Race Car Wings: A CFD Study.

Degree: 2016, Grand Valley State University

URL: https://scholarworks.gvsu.edu/theses/798

► Formula 1 racing is one of the most advanced technological sports. The aerodynamic on open wheel race cars is essential for the performance during a… (more)

▼ Formula 1 racing is one of the most advanced technological sports. The aerodynamic on open wheel race cars is essential for the performance during a race. The front wing on a race car produces about 30 percent of the entire downforce of a race car. Several studies on front wings for open wheel race cars are conducted by various authors. A number of research studies include single element airfoils in ground effect and undisturbed flow. Numerical and experimental studies show that by decreasing the ground clearance, the downforce increases. The most efficient ground clearance is reported to be approximately 10 percent of the chord length. Another effective parameter to increase the downforce is the increase of angle of attack. Both increase of angle of attack and decrease of ground clearance result in an increasing of drag. Experimental studies on race car front wings have been carried out in disturbed flow. As soon as a wing operates in a wake, a significant change on the aerodynamic forces can be found. This aerodynamic study of race car wings will focus on a wing operating in a wake. The wing model is analyzed prior in freestream and ground effect only. The study in ground effect shows a maximum downforce at a ground clearance of 22 percent of the chord length. The study in a wake consists of different ground clearance levels and different distances between a bluff body and the analyzed wing. At a distance of 10 percent of a car length, both downforce and drag experience a significant decrease compared to undisturbed flow. While moving the wing further downstream, the lift and drag coefficient recover towards the values of a wing operating in ground effect only. The most efficient ground clearance point moves from 22 percent to 25 percent of the chord length at a distance of 30, respectively 50 percent of a car length. The flow structure analysis clearly showed a positive impact of the wing tip vortices coming from the bluff body. All studies are performed using Star CCM+, a commercial CFD code developed by CD Adapco.

Subjects/Keywords: CFD; race car wing; aerodynamics; race car wing operating in ground effect; race car wing operating in wake; Engineering

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APA (6^th Edition):

Durrer, S. (2016). Aerodynamics of Race Car Wings: A CFD Study. (Thesis). Grand Valley State University. Retrieved from https://scholarworks.gvsu.edu/theses/798

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):

Durrer, Simon. “Aerodynamics of Race Car Wings: A CFD Study.” 2016. Thesis, Grand Valley State University. Accessed January 25, 2021. https://scholarworks.gvsu.edu/theses/798.

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

MLA Handbook (7^th Edition):

Durrer, Simon. “Aerodynamics of Race Car Wings: A CFD Study.” 2016. Web. 25 Jan 2021.

Vancouver:

Durrer S. Aerodynamics of Race Car Wings: A CFD Study. [Internet] [Thesis]. Grand Valley State University; 2016. [cited 2021 Jan 25]. Available from: https://scholarworks.gvsu.edu/theses/798.

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

Council of Science Editors:

Durrer S. Aerodynamics of Race Car Wings: A CFD Study. [Thesis]. Grand Valley State University; 2016. Available from: https://scholarworks.gvsu.edu/theses/798

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

University of Michigan

29. Bons, Nicolas. High-Fidelity Wing Design Exploration with Gradient-Based Optimization.

Degree: PhD, Aerospace Engineering, 2020, University of Michigan

URL: http://hdl.handle.net/2027.42/163242

► Numerical optimization has been applied to wing design problems for over 40 years. Over the decades, the scope and detail of optimization problems have advanced… (more)

▼ Numerical optimization has been applied to wing design problems for over 40 years. Over the decades, the scope and detail of optimization problems have advanced considerably. At the present time, the state-of-the-art in wing design optimization incorporates high-fidelity modeling of the steady-state aeroelastic response of the wing at both on-design and off-design operating conditions. Reynolds-averaged solutions of the Navier–Stokes equations coupled with linear finite element anal- ysis offer the highest fidelity modeling currently tenable in an optimization con- text. However, the complexity of implementing and cost of executing high-fidelity aerostructural optimization have limited the extent of research on the topic. The goal of this dissertation is to examine the general application of these tools to wing design problems and highlight several factors pertaining to their usefulness and versatility. Two types of wing design problems are considered in this dissertation: refin- ing and exploratory. Refining problems are more common in practice, especially for high-fidelity optimization, because they start from a good design and make small changes to improve it. Exploratory problems are intended to have liberal parametrizations predisposed to have significant differences between the original and final designs. The investigation of exploratory problems yields novel findings regarding multimodality in the design space and robustness of the framework. Multimodality in the design space can impact the usefulness and versatility of gradient-based optimization in wing design. Both aerodynamic and aerostructural wing design problems are shown to be amenable to gradient-based optimization despite the existence of multimodality in some cases. For example, a rectangular wing with constant cross-section is successfully converted, through gradient-based optimization, into a swept-back wing with transonic airfoils and a minimum-mass structure. These studies introduce new insights into the tradeoff between skin- friction and induced drag and its impact on multimodality and optimization. The results of these studies indicate that multimodality is dependent on model fidelity and geometric parametrization. It is shown that artificial multimodality can be eliminated by improving model fidelity and numerical accuracy of functions and derivatives, whereas physically significant multimodality can be controlled with the application of geometric constraints. The usefulness of numerical optimization in wing design hinges on the ability of the optimizer to competently balance fundamental tradeoffs. With comprehensive access to the relevant design parameters and physics models of the aerostructural system, an optimizer can converge to a better multidisciplinary design than is pos- sible with a traditional, sequential design process. This dissertation features the high-fidelity aerostructural optimization of an Embraer regional jet, in which si- multaneous optimization of airfoil shape, planform, and structural sizing variables yields a… Advisors/Committee Members: Mader, Charles (committee member), Martins, Joaquim R R A (committee member), Young, Yin Lu (committee member), Cesnik, Carlos E (committee member).

Subjects/Keywords: multidisciplinary design optimization; aerostructural optimization; wing design optimization; multimodality in wing design; practical wing design optimization; Aerospace Engineering; Engineering

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

APA (6^th Edition):

Bons, N. (2020). High-Fidelity Wing Design Exploration with Gradient-Based Optimization. (Doctoral Dissertation). University of Michigan. Retrieved from http://hdl.handle.net/2027.42/163242

Chicago Manual of Style (16^th Edition):

Bons, Nicolas. “High-Fidelity Wing Design Exploration with Gradient-Based Optimization.” 2020. Doctoral Dissertation, University of Michigan. Accessed January 25, 2021. http://hdl.handle.net/2027.42/163242.

MLA Handbook (7^th Edition):

Bons, Nicolas. “High-Fidelity Wing Design Exploration with Gradient-Based Optimization.” 2020. Web. 25 Jan 2021.

Vancouver:

Bons N. High-Fidelity Wing Design Exploration with Gradient-Based Optimization. [Internet] [Doctoral dissertation]. University of Michigan; 2020. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/2027.42/163242.

Council of Science Editors:

Bons N. High-Fidelity Wing Design Exploration with Gradient-Based Optimization. [Doctoral Dissertation]. University of Michigan; 2020. Available from: http://hdl.handle.net/2027.42/163242

Michigan State University

30. Fitzgerald, Sarah. The impact of religion on domestic right wing extremist groups and organizational violence.

Degree: 2011, Michigan State University

URL: http://etd.lib.msu.edu/islandora/object/etd:441

►

Thesis M.S. Michigan State University. Criminal Justice 2011.

The purpose of this study is to investigate the relationship between religion and violent activity among domestic… (more)

Subjects/Keywords: Right-wing extremists – United States; Right-wing extremists – United States – Religious aspects; Organizational sociology; Right-wing extremists; Criminology; Religion

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APA (6^th Edition):

Fitzgerald, S. (2011). The impact of religion on domestic right wing extremist groups and organizational violence. (Thesis). Michigan State University. Retrieved from http://etd.lib.msu.edu/islandora/object/etd:441

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):

Fitzgerald, Sarah. “The impact of religion on domestic right wing extremist groups and organizational violence.” 2011. Thesis, Michigan State University. Accessed January 25, 2021. http://etd.lib.msu.edu/islandora/object/etd:441.

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

MLA Handbook (7^th Edition):

Fitzgerald, Sarah. “The impact of religion on domestic right wing extremist groups and organizational violence.” 2011. Web. 25 Jan 2021.

Vancouver:

Fitzgerald S. The impact of religion on domestic right wing extremist groups and organizational violence. [Internet] [Thesis]. Michigan State University; 2011. [cited 2021 Jan 25]. Available from: http://etd.lib.msu.edu/islandora/object/etd:441.

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

Council of Science Editors:

Fitzgerald S. The impact of religion on domestic right wing extremist groups and organizational violence. [Thesis]. Michigan State University; 2011. Available from: http://etd.lib.msu.edu/islandora/object/etd:441

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

Open Access Theses and Dissertations