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You searched for subject:(aeroelasticity). Showing records 1 – 30 of 247 total matches.

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1. Peristy, Luke H. EXAMINATION OF SMALL AND LARGE AMPLITUDE AEROELASTIC OSCILLATIONS IN PITCH OF A NACA0012 AIRFOIL.

Degree: MASc (Master of Applied Science/Ma??trise ??s sciences appliqu??es), Mechanical Engineering/G??nie m??canique, 2016, Royal Military College of Canada

One degree of freedom aeroelastic oscillations in pitch of a NACA0012 airfoil at transitional Reynolds numbers were examined experimentally in a wind tunnel using a… (more)

Subjects/Keywords: Aeroelasticity

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

APA (6th Edition):

Peristy, L. H. (2016). EXAMINATION OF SMALL AND LARGE AMPLITUDE AEROELASTIC OSCILLATIONS IN PITCH OF A NACA0012 AIRFOIL. (Masters Thesis). Royal Military College of Canada. Retrieved from http://hdl.handle.net/11264/882

Chicago Manual of Style (16th Edition):

Peristy, Luke H. “EXAMINATION OF SMALL AND LARGE AMPLITUDE AEROELASTIC OSCILLATIONS IN PITCH OF A NACA0012 AIRFOIL.” 2016. Masters Thesis, Royal Military College of Canada. Accessed February 23, 2020. http://hdl.handle.net/11264/882.

MLA Handbook (7th Edition):

Peristy, Luke H. “EXAMINATION OF SMALL AND LARGE AMPLITUDE AEROELASTIC OSCILLATIONS IN PITCH OF A NACA0012 AIRFOIL.” 2016. Web. 23 Feb 2020.

Vancouver:

Peristy LH. EXAMINATION OF SMALL AND LARGE AMPLITUDE AEROELASTIC OSCILLATIONS IN PITCH OF A NACA0012 AIRFOIL. [Internet] [Masters thesis]. Royal Military College of Canada; 2016. [cited 2020 Feb 23]. Available from: http://hdl.handle.net/11264/882.

Council of Science Editors:

Peristy LH. EXAMINATION OF SMALL AND LARGE AMPLITUDE AEROELASTIC OSCILLATIONS IN PITCH OF A NACA0012 AIRFOIL. [Masters Thesis]. Royal Military College of Canada; 2016. Available from: http://hdl.handle.net/11264/882


Texas A&M University

2. Gargoloff, Joaquin Ivan. A numerical method for fully nonlinear aeroelastic analysis.

Degree: 2009, Texas A&M University

 This work presents a numerical method for the analysis of fully nonlinear aeroelastic problems. The aeroelastic model consisted of a Navier-Stokes flow solver, a nonlinear… (more)

Subjects/Keywords: aeroelasticity; cfd

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APA (6th Edition):

Gargoloff, J. I. (2009). A numerical method for fully nonlinear aeroelastic analysis. (Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/ETD-TAMU-1219

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

Chicago Manual of Style (16th Edition):

Gargoloff, Joaquin Ivan. “A numerical method for fully nonlinear aeroelastic analysis.” 2009. Thesis, Texas A&M University. Accessed February 23, 2020. http://hdl.handle.net/1969.1/ETD-TAMU-1219.

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

MLA Handbook (7th Edition):

Gargoloff, Joaquin Ivan. “A numerical method for fully nonlinear aeroelastic analysis.” 2009. Web. 23 Feb 2020.

Vancouver:

Gargoloff JI. A numerical method for fully nonlinear aeroelastic analysis. [Internet] [Thesis]. Texas A&M University; 2009. [cited 2020 Feb 23]. Available from: http://hdl.handle.net/1969.1/ETD-TAMU-1219.

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

Council of Science Editors:

Gargoloff JI. A numerical method for fully nonlinear aeroelastic analysis. [Thesis]. Texas A&M University; 2009. Available from: http://hdl.handle.net/1969.1/ETD-TAMU-1219

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


KTH

3. Bernardi, Giacomo. Feasibility Study of a 3D CFD Solution for FSI Investigations on NREL 5MW Wind Turbine Blade.

Degree: Heat and Power Technology, 2015, KTH

  With the increase in length of wind turbine blades flutter is becoming a potential design constrain, hence the interest in computational tools for fluid-structure… (more)

Subjects/Keywords: HAWT; CFD; Aeroelasticity

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APA (6th Edition):

Bernardi, G. (2015). Feasibility Study of a 3D CFD Solution for FSI Investigations on NREL 5MW Wind Turbine Blade. (Thesis). KTH. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-159690

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

Chicago Manual of Style (16th Edition):

Bernardi, Giacomo. “Feasibility Study of a 3D CFD Solution for FSI Investigations on NREL 5MW Wind Turbine Blade.” 2015. Thesis, KTH. Accessed February 23, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-159690.

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

MLA Handbook (7th Edition):

Bernardi, Giacomo. “Feasibility Study of a 3D CFD Solution for FSI Investigations on NREL 5MW Wind Turbine Blade.” 2015. Web. 23 Feb 2020.

Vancouver:

Bernardi G. Feasibility Study of a 3D CFD Solution for FSI Investigations on NREL 5MW Wind Turbine Blade. [Internet] [Thesis]. KTH; 2015. [cited 2020 Feb 23]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-159690.

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

Council of Science Editors:

Bernardi G. Feasibility Study of a 3D CFD Solution for FSI Investigations on NREL 5MW Wind Turbine Blade. [Thesis]. KTH; 2015. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-159690

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


The Ohio State University

4. Swaim, Robert Lee. Active control of booster elasticity.

Degree: PhD, Graduate School, 1966, The Ohio State University

Subjects/Keywords: Engineering; Aeroelasticity

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APA (6th Edition):

Swaim, R. L. (1966). Active control of booster elasticity. (Doctoral Dissertation). The Ohio State University. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=osu1486634509114617

Chicago Manual of Style (16th Edition):

Swaim, Robert Lee. “Active control of booster elasticity.” 1966. Doctoral Dissertation, The Ohio State University. Accessed February 23, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=osu1486634509114617.

MLA Handbook (7th Edition):

Swaim, Robert Lee. “Active control of booster elasticity.” 1966. Web. 23 Feb 2020.

Vancouver:

Swaim RL. Active control of booster elasticity. [Internet] [Doctoral dissertation]. The Ohio State University; 1966. [cited 2020 Feb 23]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1486634509114617.

Council of Science Editors:

Swaim RL. Active control of booster elasticity. [Doctoral Dissertation]. The Ohio State University; 1966. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1486634509114617


University of New Mexico

5. Carter, Melissa. Effect of an aeroelastic film on confined subsonic cavity resonance.

Degree: Mechanical Engineering, 2011, University of New Mexico

 EFFECT OF AN AEROELASTIC FILM ON CONFINED SUBSONIC CAVITY RESONANCE by Melissa Carter B.S., Mechanical Engineering, University of New Mexico, 2001 M.S., Mechanical Engineering, University… (more)

Subjects/Keywords: Thin films; Aeroelasticity; Resonators; Cavity.

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APA (6th Edition):

Carter, M. (2011). Effect of an aeroelastic film on confined subsonic cavity resonance. (Masters Thesis). University of New Mexico. Retrieved from http://hdl.handle.net/1928/12833

Chicago Manual of Style (16th Edition):

Carter, Melissa. “Effect of an aeroelastic film on confined subsonic cavity resonance.” 2011. Masters Thesis, University of New Mexico. Accessed February 23, 2020. http://hdl.handle.net/1928/12833.

MLA Handbook (7th Edition):

Carter, Melissa. “Effect of an aeroelastic film on confined subsonic cavity resonance.” 2011. Web. 23 Feb 2020.

Vancouver:

Carter M. Effect of an aeroelastic film on confined subsonic cavity resonance. [Internet] [Masters thesis]. University of New Mexico; 2011. [cited 2020 Feb 23]. Available from: http://hdl.handle.net/1928/12833.

Council of Science Editors:

Carter M. Effect of an aeroelastic film on confined subsonic cavity resonance. [Masters Thesis]. University of New Mexico; 2011. Available from: http://hdl.handle.net/1928/12833


UCLA

6. Mellquist, Erik Charles. Computational Transonic Flutter Solutions for Cranked Wings by the Direct Eulerian-Lagrangian Method.

Degree: Aerospace Engineering, 2014, UCLA

 In this dissertation, a three-dimensional computational aeroelastic simulation for cranked, highly-swept wings is developed, and solutions are presented for several wing models. The computational model… (more)

Subjects/Keywords: Aerospace engineering; aeroelasticity; flutter; transonic

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APA (6th Edition):

Mellquist, E. C. (2014). Computational Transonic Flutter Solutions for Cranked Wings by the Direct Eulerian-Lagrangian Method. (Thesis). UCLA. Retrieved from http://www.escholarship.org/uc/item/9rk54186

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

Chicago Manual of Style (16th Edition):

Mellquist, Erik Charles. “Computational Transonic Flutter Solutions for Cranked Wings by the Direct Eulerian-Lagrangian Method.” 2014. Thesis, UCLA. Accessed February 23, 2020. http://www.escholarship.org/uc/item/9rk54186.

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

MLA Handbook (7th Edition):

Mellquist, Erik Charles. “Computational Transonic Flutter Solutions for Cranked Wings by the Direct Eulerian-Lagrangian Method.” 2014. Web. 23 Feb 2020.

Vancouver:

Mellquist EC. Computational Transonic Flutter Solutions for Cranked Wings by the Direct Eulerian-Lagrangian Method. [Internet] [Thesis]. UCLA; 2014. [cited 2020 Feb 23]. Available from: http://www.escholarship.org/uc/item/9rk54186.

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

Council of Science Editors:

Mellquist EC. Computational Transonic Flutter Solutions for Cranked Wings by the Direct Eulerian-Lagrangian Method. [Thesis]. UCLA; 2014. Available from: http://www.escholarship.org/uc/item/9rk54186

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


Virginia Tech

7. Ricciardi, Anthony Pasquale. Utility of Quasi-Static Gust Loads Certification Methods for Novel Configurations.

Degree: MS, Aerospace and Ocean Engineering, 2011, Virginia Tech

 Aeroelastic gust and maneuver loads have driven the sizing of primary aircraft structures since the beginning of aviation. Methodologies for determining the gust loads on… (more)

Subjects/Keywords: SensorCraft; Aeroelasticity; Gust Loads

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APA (6th Edition):

Ricciardi, A. P. (2011). Utility of Quasi-Static Gust Loads Certification Methods for Novel Configurations. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/35359

Chicago Manual of Style (16th Edition):

Ricciardi, Anthony Pasquale. “Utility of Quasi-Static Gust Loads Certification Methods for Novel Configurations.” 2011. Masters Thesis, Virginia Tech. Accessed February 23, 2020. http://hdl.handle.net/10919/35359.

MLA Handbook (7th Edition):

Ricciardi, Anthony Pasquale. “Utility of Quasi-Static Gust Loads Certification Methods for Novel Configurations.” 2011. Web. 23 Feb 2020.

Vancouver:

Ricciardi AP. Utility of Quasi-Static Gust Loads Certification Methods for Novel Configurations. [Internet] [Masters thesis]. Virginia Tech; 2011. [cited 2020 Feb 23]. Available from: http://hdl.handle.net/10919/35359.

Council of Science Editors:

Ricciardi AP. Utility of Quasi-Static Gust Loads Certification Methods for Novel Configurations. [Masters Thesis]. Virginia Tech; 2011. Available from: http://hdl.handle.net/10919/35359


Virginia Tech

8. Butt, Lauren Marie. Design Optimization of a High Aspect Ratio Rigid/Inflatable Wing.

Degree: MS, Aerospace and Ocean Engineering, 2011, Virginia Tech

 High aspect-ratio, long-endurance aircraft require different design modeling from those with traditional moderate aspect ratios. High aspect-ratio, long endurance aircraft are generally more flexible structures… (more)

Subjects/Keywords: Design Optimization; Aeroelasticity; Inflatable Wings

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APA (6th Edition):

Butt, L. M. (2011). Design Optimization of a High Aspect Ratio Rigid/Inflatable Wing. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/42641

Chicago Manual of Style (16th Edition):

Butt, Lauren Marie. “Design Optimization of a High Aspect Ratio Rigid/Inflatable Wing.” 2011. Masters Thesis, Virginia Tech. Accessed February 23, 2020. http://hdl.handle.net/10919/42641.

MLA Handbook (7th Edition):

Butt, Lauren Marie. “Design Optimization of a High Aspect Ratio Rigid/Inflatable Wing.” 2011. Web. 23 Feb 2020.

Vancouver:

Butt LM. Design Optimization of a High Aspect Ratio Rigid/Inflatable Wing. [Internet] [Masters thesis]. Virginia Tech; 2011. [cited 2020 Feb 23]. Available from: http://hdl.handle.net/10919/42641.

Council of Science Editors:

Butt LM. Design Optimization of a High Aspect Ratio Rigid/Inflatable Wing. [Masters Thesis]. Virginia Tech; 2011. Available from: http://hdl.handle.net/10919/42641


Virginia Tech

9. Ricciardi, Anthony Pasquale. Geometrically Nonlinear Aeroelastic Scaling.

Degree: PhD, Aerospace and Ocean Engineering, 2014, Virginia Tech

 Aeroelastic scaling methodologies are developed for geometrically nonlinear applications. The new methods are demonstrated by designing an aeroelastically scaled model of a suitably nonlinear full-scale… (more)

Subjects/Keywords: Nonlinear; Aeroelasticity; Scaling; SensorCraft

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APA (6th Edition):

Ricciardi, A. P. (2014). Geometrically Nonlinear Aeroelastic Scaling. (Doctoral Dissertation). Virginia Tech. Retrieved from http://hdl.handle.net/10919/24913

Chicago Manual of Style (16th Edition):

Ricciardi, Anthony Pasquale. “Geometrically Nonlinear Aeroelastic Scaling.” 2014. Doctoral Dissertation, Virginia Tech. Accessed February 23, 2020. http://hdl.handle.net/10919/24913.

MLA Handbook (7th Edition):

Ricciardi, Anthony Pasquale. “Geometrically Nonlinear Aeroelastic Scaling.” 2014. Web. 23 Feb 2020.

Vancouver:

Ricciardi AP. Geometrically Nonlinear Aeroelastic Scaling. [Internet] [Doctoral dissertation]. Virginia Tech; 2014. [cited 2020 Feb 23]. Available from: http://hdl.handle.net/10919/24913.

Council of Science Editors:

Ricciardi AP. Geometrically Nonlinear Aeroelastic Scaling. [Doctoral Dissertation]. Virginia Tech; 2014. Available from: http://hdl.handle.net/10919/24913


Delft University of Technology

10. Janssen, M. Aeroelastic Modelling of Composite Rotor Blades:.

Degree: 2015, Delft University of Technology

 This thesis was conducted at KVE Composites Group (The Hague, The Netherlands). The aim of this thesis is to create an aeroelastic model that can… (more)

Subjects/Keywords: rotor; blade; aeroelastic; modelling; aeroelasticity

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APA (6th Edition):

Janssen, M. (2015). Aeroelastic Modelling of Composite Rotor Blades:. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:316904df-d86b-415c-803a-9a94df225b21

Chicago Manual of Style (16th Edition):

Janssen, M. “Aeroelastic Modelling of Composite Rotor Blades:.” 2015. Masters Thesis, Delft University of Technology. Accessed February 23, 2020. http://resolver.tudelft.nl/uuid:316904df-d86b-415c-803a-9a94df225b21.

MLA Handbook (7th Edition):

Janssen, M. “Aeroelastic Modelling of Composite Rotor Blades:.” 2015. Web. 23 Feb 2020.

Vancouver:

Janssen M. Aeroelastic Modelling of Composite Rotor Blades:. [Internet] [Masters thesis]. Delft University of Technology; 2015. [cited 2020 Feb 23]. Available from: http://resolver.tudelft.nl/uuid:316904df-d86b-415c-803a-9a94df225b21.

Council of Science Editors:

Janssen M. Aeroelastic Modelling of Composite Rotor Blades:. [Masters Thesis]. Delft University of Technology; 2015. Available from: http://resolver.tudelft.nl/uuid:316904df-d86b-415c-803a-9a94df225b21


Virginia Tech

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

Degree: MS, Aerospace Engineering, 2013, Virginia Tech

 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 (6th 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 (16th Edition):

Eger, Charles Alfred Gaitan. “Design of a Scaled Flight Test Vehicle Including Linear Aeroelastic Effects.” 2013. Masters Thesis, Virginia Tech. Accessed February 23, 2020. http://hdl.handle.net/10919/23088.

MLA Handbook (7th Edition):

Eger, Charles Alfred Gaitan. “Design of a Scaled Flight Test Vehicle Including Linear Aeroelastic Effects.” 2013. Web. 23 Feb 2020.

Vancouver:

Eger CAG. Design of a Scaled Flight Test Vehicle Including Linear Aeroelastic Effects. [Internet] [Masters thesis]. Virginia Tech; 2013. [cited 2020 Feb 23]. 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


Texas A&M University

12. Freno, Brian Andrew. An Efficient Nonlinear Structural Dynamics Solver for Use in Computational Aeroelastic Analysis.

Degree: 2011, Texas A&M University

 Aerospace structures with large aspect ratio, such as airplane wings, rotorcraft blades, wind turbine blades, and jet engine fan and compressor blades, are particularly susceptible… (more)

Subjects/Keywords: aeroelasticity; nonlinear structural dynamics; computational aeroelasticity; elasticity; aerodynamics

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APA (6th Edition):

Freno, B. A. (2011). An Efficient Nonlinear Structural Dynamics Solver for Use in Computational Aeroelastic Analysis. (Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/ETD-TAMU-2010-05-8039

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

Chicago Manual of Style (16th Edition):

Freno, Brian Andrew. “An Efficient Nonlinear Structural Dynamics Solver for Use in Computational Aeroelastic Analysis.” 2011. Thesis, Texas A&M University. Accessed February 23, 2020. http://hdl.handle.net/1969.1/ETD-TAMU-2010-05-8039.

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

MLA Handbook (7th Edition):

Freno, Brian Andrew. “An Efficient Nonlinear Structural Dynamics Solver for Use in Computational Aeroelastic Analysis.” 2011. Web. 23 Feb 2020.

Vancouver:

Freno BA. An Efficient Nonlinear Structural Dynamics Solver for Use in Computational Aeroelastic Analysis. [Internet] [Thesis]. Texas A&M University; 2011. [cited 2020 Feb 23]. Available from: http://hdl.handle.net/1969.1/ETD-TAMU-2010-05-8039.

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

Council of Science Editors:

Freno BA. An Efficient Nonlinear Structural Dynamics Solver for Use in Computational Aeroelastic Analysis. [Thesis]. Texas A&M University; 2011. Available from: http://hdl.handle.net/1969.1/ETD-TAMU-2010-05-8039

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


University of Manchester

13. Miller, Simon James. Adaptive wing structures for aeroelastic drag reduction and loads alleviation.

Degree: PhD, 2011, University of Manchester

 An investigation into two distinct novel adaptive structures concepts is performed with a view to improving the aerodynamic efficiency of aircraft wings.The main focus of… (more)

Subjects/Keywords: 629.13; Aeroelasticity; Aircraft morphing; Adaptive wing structures

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APA (6th Edition):

Miller, S. J. (2011). Adaptive wing structures for aeroelastic drag reduction and loads alleviation. (Doctoral Dissertation). University of Manchester. Retrieved from https://www.research.manchester.ac.uk/portal/en/theses/adaptive-wing-structures-for-aeroelastic-drag-reduction-and-loadsalleviation(562181ed-7153-44cb-b0c7-9bfe1f79ae0f).html ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.542701

Chicago Manual of Style (16th Edition):

Miller, Simon James. “Adaptive wing structures for aeroelastic drag reduction and loads alleviation.” 2011. Doctoral Dissertation, University of Manchester. Accessed February 23, 2020. https://www.research.manchester.ac.uk/portal/en/theses/adaptive-wing-structures-for-aeroelastic-drag-reduction-and-loadsalleviation(562181ed-7153-44cb-b0c7-9bfe1f79ae0f).html ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.542701.

MLA Handbook (7th Edition):

Miller, Simon James. “Adaptive wing structures for aeroelastic drag reduction and loads alleviation.” 2011. Web. 23 Feb 2020.

Vancouver:

Miller SJ. Adaptive wing structures for aeroelastic drag reduction and loads alleviation. [Internet] [Doctoral dissertation]. University of Manchester; 2011. [cited 2020 Feb 23]. Available from: https://www.research.manchester.ac.uk/portal/en/theses/adaptive-wing-structures-for-aeroelastic-drag-reduction-and-loadsalleviation(562181ed-7153-44cb-b0c7-9bfe1f79ae0f).html ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.542701.

Council of Science Editors:

Miller SJ. Adaptive wing structures for aeroelastic drag reduction and loads alleviation. [Doctoral Dissertation]. University of Manchester; 2011. Available from: https://www.research.manchester.ac.uk/portal/en/theses/adaptive-wing-structures-for-aeroelastic-drag-reduction-and-loadsalleviation(562181ed-7153-44cb-b0c7-9bfe1f79ae0f).html ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.542701


University of Manchester

14. Miller, Simon James. Adaptive wing structures for aeroelastic drag reduction and loadsalleviation.

Degree: 2011, University of Manchester

 An investigation into two distinct novel adaptive structures concepts is performed with a view to improving the aerodynamic efficiency of aircraft wings.The main focus of… (more)

Subjects/Keywords: Aeroelasticity; Aircraft morphing; Adaptive wing structures

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APA (6th Edition):

Miller, S. J. (2011). Adaptive wing structures for aeroelastic drag reduction and loadsalleviation. (Doctoral Dissertation). University of Manchester. Retrieved from http://www.manchester.ac.uk/escholar/uk-ac-man-scw:120148

Chicago Manual of Style (16th Edition):

Miller, Simon James. “Adaptive wing structures for aeroelastic drag reduction and loadsalleviation.” 2011. Doctoral Dissertation, University of Manchester. Accessed February 23, 2020. http://www.manchester.ac.uk/escholar/uk-ac-man-scw:120148.

MLA Handbook (7th Edition):

Miller, Simon James. “Adaptive wing structures for aeroelastic drag reduction and loadsalleviation.” 2011. Web. 23 Feb 2020.

Vancouver:

Miller SJ. Adaptive wing structures for aeroelastic drag reduction and loadsalleviation. [Internet] [Doctoral dissertation]. University of Manchester; 2011. [cited 2020 Feb 23]. Available from: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:120148.

Council of Science Editors:

Miller SJ. Adaptive wing structures for aeroelastic drag reduction and loadsalleviation. [Doctoral Dissertation]. University of Manchester; 2011. Available from: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:120148


University of British Columbia

15. Slater, Jonathan Ernest. Aeroelastic instability of a structural angle section .

Degree: 1969, University of British Columbia

 Angle section members, used in open engineering structures, have been known to experience large amplitude oscillations when exposed to normal atmospheric winds, and in a… (more)

Subjects/Keywords: Aeroelasticity; Angles  – Vibration

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APA (6th Edition):

Slater, J. E. (1969). Aeroelastic instability of a structural angle section . (Thesis). University of British Columbia. Retrieved from http://hdl.handle.net/2429/35618

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

Chicago Manual of Style (16th Edition):

Slater, Jonathan Ernest. “Aeroelastic instability of a structural angle section .” 1969. Thesis, University of British Columbia. Accessed February 23, 2020. http://hdl.handle.net/2429/35618.

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

MLA Handbook (7th Edition):

Slater, Jonathan Ernest. “Aeroelastic instability of a structural angle section .” 1969. Web. 23 Feb 2020.

Vancouver:

Slater JE. Aeroelastic instability of a structural angle section . [Internet] [Thesis]. University of British Columbia; 1969. [cited 2020 Feb 23]. Available from: http://hdl.handle.net/2429/35618.

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

Council of Science Editors:

Slater JE. Aeroelastic instability of a structural angle section . [Thesis]. University of British Columbia; 1969. Available from: http://hdl.handle.net/2429/35618

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


Texas A&M University

16. Long, Robert Raymond. Experiments on Dynamic Aeroelastic Response of Wind Turbine Blades.

Degree: PhD, Aerospace Engineering, 2017, Texas A&M University

 Wind turbine blades are growing progressively larger and lighter relative to their size, and these trends can lead to early failure due to fatigue. Effort… (more)

Subjects/Keywords: wind turbine; aeroelasticity; wind tunnel; experimental

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APA (6th Edition):

Long, R. R. (2017). Experiments on Dynamic Aeroelastic Response of Wind Turbine Blades. (Doctoral Dissertation). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/173080

Chicago Manual of Style (16th Edition):

Long, Robert Raymond. “Experiments on Dynamic Aeroelastic Response of Wind Turbine Blades.” 2017. Doctoral Dissertation, Texas A&M University. Accessed February 23, 2020. http://hdl.handle.net/1969.1/173080.

MLA Handbook (7th Edition):

Long, Robert Raymond. “Experiments on Dynamic Aeroelastic Response of Wind Turbine Blades.” 2017. Web. 23 Feb 2020.

Vancouver:

Long RR. Experiments on Dynamic Aeroelastic Response of Wind Turbine Blades. [Internet] [Doctoral dissertation]. Texas A&M University; 2017. [cited 2020 Feb 23]. Available from: http://hdl.handle.net/1969.1/173080.

Council of Science Editors:

Long RR. Experiments on Dynamic Aeroelastic Response of Wind Turbine Blades. [Doctoral Dissertation]. Texas A&M University; 2017. Available from: http://hdl.handle.net/1969.1/173080


Delft University of Technology

17. Natella, M. Coupled Nonlinear Aeroelasticity and Flight Dynamics for Stability Analysis of Flexible Wing Structures:.

Degree: 2015, Delft University of Technology

 The present work thus develops a low-fidelity formulation to investigate the flight dynamic stability of a flexible wing structure. The model is verified against other… (more)

Subjects/Keywords: aeroelasticity; flight dynamics; flexible wings; stability analysis

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APA (6th Edition):

Natella, M. (2015). Coupled Nonlinear Aeroelasticity and Flight Dynamics for Stability Analysis of Flexible Wing Structures:. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:39984220-1d55-43fb-b42c-8a692a979211

Chicago Manual of Style (16th Edition):

Natella, M. “Coupled Nonlinear Aeroelasticity and Flight Dynamics for Stability Analysis of Flexible Wing Structures:.” 2015. Masters Thesis, Delft University of Technology. Accessed February 23, 2020. http://resolver.tudelft.nl/uuid:39984220-1d55-43fb-b42c-8a692a979211.

MLA Handbook (7th Edition):

Natella, M. “Coupled Nonlinear Aeroelasticity and Flight Dynamics for Stability Analysis of Flexible Wing Structures:.” 2015. Web. 23 Feb 2020.

Vancouver:

Natella M. Coupled Nonlinear Aeroelasticity and Flight Dynamics for Stability Analysis of Flexible Wing Structures:. [Internet] [Masters thesis]. Delft University of Technology; 2015. [cited 2020 Feb 23]. Available from: http://resolver.tudelft.nl/uuid:39984220-1d55-43fb-b42c-8a692a979211.

Council of Science Editors:

Natella M. Coupled Nonlinear Aeroelasticity and Flight Dynamics for Stability Analysis of Flexible Wing Structures:. [Masters Thesis]. Delft University of Technology; 2015. Available from: http://resolver.tudelft.nl/uuid:39984220-1d55-43fb-b42c-8a692a979211


Delft University of Technology

18. Kalthof, R.L.C. Multibody Dynamics Modeling of Flexible Aircraft Flight Dynamics:.

Degree: 2014, Delft University of Technology

 Because of the focus on weight minimization, aircraft are becoming more and more flexible. Therefore, the frequency separation between flight mechanics motion and structural vibration… (more)

Subjects/Keywords: multibody dynamics; aeroelasticity; SimMechanics; flight dynamics

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APA (6th Edition):

Kalthof, R. L. C. (2014). Multibody Dynamics Modeling of Flexible Aircraft Flight Dynamics:. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:6aa1d6a0-0601-4595-97b3-047117fc6a97

Chicago Manual of Style (16th Edition):

Kalthof, R L C. “Multibody Dynamics Modeling of Flexible Aircraft Flight Dynamics:.” 2014. Masters Thesis, Delft University of Technology. Accessed February 23, 2020. http://resolver.tudelft.nl/uuid:6aa1d6a0-0601-4595-97b3-047117fc6a97.

MLA Handbook (7th Edition):

Kalthof, R L C. “Multibody Dynamics Modeling of Flexible Aircraft Flight Dynamics:.” 2014. Web. 23 Feb 2020.

Vancouver:

Kalthof RLC. Multibody Dynamics Modeling of Flexible Aircraft Flight Dynamics:. [Internet] [Masters thesis]. Delft University of Technology; 2014. [cited 2020 Feb 23]. Available from: http://resolver.tudelft.nl/uuid:6aa1d6a0-0601-4595-97b3-047117fc6a97.

Council of Science Editors:

Kalthof RLC. Multibody Dynamics Modeling of Flexible Aircraft Flight Dynamics:. [Masters Thesis]. Delft University of Technology; 2014. Available from: http://resolver.tudelft.nl/uuid:6aa1d6a0-0601-4595-97b3-047117fc6a97


University of Minnesota

19. Alfifi, Salman. An Experimental Study of Wing Flutter.

Degree: PhD, Aerospace Engineering and Mechanics, 2017, University of Minnesota

 While many experimental studies use springs to model the bending and torsional motions of a fluttered wing in wind tunnel experiments, the mass of the… (more)

Subjects/Keywords: aerodynamics; aeroelasticity; flluid mechanics; flutter; wing

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APA (6th Edition):

Alfifi, S. (2017). An Experimental Study of Wing Flutter. (Doctoral Dissertation). University of Minnesota. Retrieved from http://hdl.handle.net/11299/206344

Chicago Manual of Style (16th Edition):

Alfifi, Salman. “An Experimental Study of Wing Flutter.” 2017. Doctoral Dissertation, University of Minnesota. Accessed February 23, 2020. http://hdl.handle.net/11299/206344.

MLA Handbook (7th Edition):

Alfifi, Salman. “An Experimental Study of Wing Flutter.” 2017. Web. 23 Feb 2020.

Vancouver:

Alfifi S. An Experimental Study of Wing Flutter. [Internet] [Doctoral dissertation]. University of Minnesota; 2017. [cited 2020 Feb 23]. Available from: http://hdl.handle.net/11299/206344.

Council of Science Editors:

Alfifi S. An Experimental Study of Wing Flutter. [Doctoral Dissertation]. University of Minnesota; 2017. Available from: http://hdl.handle.net/11299/206344


Georgia Tech

20. Chae, Seungmook. Effect of Follower Forces on Aeroelastic Stability of Flexible Structures.

Degree: PhD, Aerospace Engineering, 2004, Georgia Tech

 Missile bodies and wings are typical examples of structures that can be represented by beam models. Such structures, loaded by follower forces along with aerodynamics,… (more)

Subjects/Keywords: Aeroelasticity; Follower force

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APA (6th Edition):

Chae, S. (2004). Effect of Follower Forces on Aeroelastic Stability of Flexible Structures. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/5037

Chicago Manual of Style (16th Edition):

Chae, Seungmook. “Effect of Follower Forces on Aeroelastic Stability of Flexible Structures.” 2004. Doctoral Dissertation, Georgia Tech. Accessed February 23, 2020. http://hdl.handle.net/1853/5037.

MLA Handbook (7th Edition):

Chae, Seungmook. “Effect of Follower Forces on Aeroelastic Stability of Flexible Structures.” 2004. Web. 23 Feb 2020.

Vancouver:

Chae S. Effect of Follower Forces on Aeroelastic Stability of Flexible Structures. [Internet] [Doctoral dissertation]. Georgia Tech; 2004. [cited 2020 Feb 23]. Available from: http://hdl.handle.net/1853/5037.

Council of Science Editors:

Chae S. Effect of Follower Forces on Aeroelastic Stability of Flexible Structures. [Doctoral Dissertation]. Georgia Tech; 2004. Available from: http://hdl.handle.net/1853/5037


University of Pretoria

21. Meijer, Marius-Corne. Development of an Aeroprediction Method for Slender Bodies Including Aeroelastic Effects Using Euler-Based Local Piston Theory.

Degree: PhD, Mechanical and Aeronautical Engineering, 2019, University of Pretoria

 Euler-based local piston theory (LPT) has received significant interest in recent literature. The method utilizes a simple, algebraic relation to predict between perturbation pressures directly… (more)

Subjects/Keywords: Aerodynamics; UCTD; Aeroelasticity

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APA (6th Edition):

Meijer, M. (2019). Development of an Aeroprediction Method for Slender Bodies Including Aeroelastic Effects Using Euler-Based Local Piston Theory. (Doctoral Dissertation). University of Pretoria. Retrieved from http://hdl.handle.net/2263/68727

Chicago Manual of Style (16th Edition):

Meijer, Marius-Corne. “Development of an Aeroprediction Method for Slender Bodies Including Aeroelastic Effects Using Euler-Based Local Piston Theory.” 2019. Doctoral Dissertation, University of Pretoria. Accessed February 23, 2020. http://hdl.handle.net/2263/68727.

MLA Handbook (7th Edition):

Meijer, Marius-Corne. “Development of an Aeroprediction Method for Slender Bodies Including Aeroelastic Effects Using Euler-Based Local Piston Theory.” 2019. Web. 23 Feb 2020.

Vancouver:

Meijer M. Development of an Aeroprediction Method for Slender Bodies Including Aeroelastic Effects Using Euler-Based Local Piston Theory. [Internet] [Doctoral dissertation]. University of Pretoria; 2019. [cited 2020 Feb 23]. Available from: http://hdl.handle.net/2263/68727.

Council of Science Editors:

Meijer M. Development of an Aeroprediction Method for Slender Bodies Including Aeroelastic Effects Using Euler-Based Local Piston Theory. [Doctoral Dissertation]. University of Pretoria; 2019. Available from: http://hdl.handle.net/2263/68727

22. Král Radomil. Numerical and experimental solutions of self-induced instability of bridge .

Degree: 2011, Czech University of Technology

 The thesis is focused on a solution of self-induced oscillations and instabilities of slender beams in the wind. It uses a combination of appropriately selected… (more)

Subjects/Keywords: bridge aeroelasticity; flutter instability; wind-structure interaction; bluff body.

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APA (6th Edition):

Radomil, K. (2011). Numerical and experimental solutions of self-induced instability of bridge . (Thesis). Czech University of Technology. Retrieved from http://hdl.handle.net/10467/8083

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

Chicago Manual of Style (16th Edition):

Radomil, Král. “Numerical and experimental solutions of self-induced instability of bridge .” 2011. Thesis, Czech University of Technology. Accessed February 23, 2020. http://hdl.handle.net/10467/8083.

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

MLA Handbook (7th Edition):

Radomil, Král. “Numerical and experimental solutions of self-induced instability of bridge .” 2011. Web. 23 Feb 2020.

Vancouver:

Radomil K. Numerical and experimental solutions of self-induced instability of bridge . [Internet] [Thesis]. Czech University of Technology; 2011. [cited 2020 Feb 23]. Available from: http://hdl.handle.net/10467/8083.

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

Council of Science Editors:

Radomil K. Numerical and experimental solutions of self-induced instability of bridge . [Thesis]. Czech University of Technology; 2011. Available from: http://hdl.handle.net/10467/8083

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

23. Bidinotto, Jorge Henrique. Proposta conceitual de excitador de \"flutter\" alternativo para ensaios em vôo.

Degree: Mestrado, Aeronaves, 2007, University of São Paulo

Os novos materiais utilizados nas estruturas de aeronaves, mais leves e flexíveis, tornam estas estruturas mais sujeitas a fenômenos aeroelásticos, sendo que o mais sério… (more)

Subjects/Keywords: Aeroelasticidade; Aeroelasticity; Ensaios em vôo; Excitador; Exciter; Flight test; Flutter; Flutter

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APA (6th Edition):

Bidinotto, J. H. (2007). Proposta conceitual de excitador de \"flutter\" alternativo para ensaios em vôo. (Masters Thesis). University of São Paulo. Retrieved from http://www.teses.usp.br/teses/disponiveis/18/18148/tde-27052009-142508/ ;

Chicago Manual of Style (16th Edition):

Bidinotto, Jorge Henrique. “Proposta conceitual de excitador de \"flutter\" alternativo para ensaios em vôo.” 2007. Masters Thesis, University of São Paulo. Accessed February 23, 2020. http://www.teses.usp.br/teses/disponiveis/18/18148/tde-27052009-142508/ ;.

MLA Handbook (7th Edition):

Bidinotto, Jorge Henrique. “Proposta conceitual de excitador de \"flutter\" alternativo para ensaios em vôo.” 2007. Web. 23 Feb 2020.

Vancouver:

Bidinotto JH. Proposta conceitual de excitador de \"flutter\" alternativo para ensaios em vôo. [Internet] [Masters thesis]. University of São Paulo; 2007. [cited 2020 Feb 23]. Available from: http://www.teses.usp.br/teses/disponiveis/18/18148/tde-27052009-142508/ ;.

Council of Science Editors:

Bidinotto JH. Proposta conceitual de excitador de \"flutter\" alternativo para ensaios em vôo. [Masters Thesis]. University of São Paulo; 2007. Available from: http://www.teses.usp.br/teses/disponiveis/18/18148/tde-27052009-142508/ ;


Texas A&M University

24. Nichkawde, Chetan. Nonlinear aeroelastic analysis of high aspect-ratio wings using the method of numerical continuation.

Degree: 2006, Texas A&M University

 This research explores the impact of kinematic structural nonlinearities on the dynamics of a highly deformable cantilevered wing. Two different theoretical formulations are presented and… (more)

Subjects/Keywords: Aeroelasticity; Nonlinear; Continuation; Bifurcation

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APA (6th Edition):

Nichkawde, C. (2006). Nonlinear aeroelastic analysis of high aspect-ratio wings using the method of numerical continuation. (Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/3846

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

Chicago Manual of Style (16th Edition):

Nichkawde, Chetan. “Nonlinear aeroelastic analysis of high aspect-ratio wings using the method of numerical continuation.” 2006. Thesis, Texas A&M University. Accessed February 23, 2020. http://hdl.handle.net/1969.1/3846.

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

MLA Handbook (7th Edition):

Nichkawde, Chetan. “Nonlinear aeroelastic analysis of high aspect-ratio wings using the method of numerical continuation.” 2006. Web. 23 Feb 2020.

Vancouver:

Nichkawde C. Nonlinear aeroelastic analysis of high aspect-ratio wings using the method of numerical continuation. [Internet] [Thesis]. Texas A&M University; 2006. [cited 2020 Feb 23]. Available from: http://hdl.handle.net/1969.1/3846.

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

Council of Science Editors:

Nichkawde C. Nonlinear aeroelastic analysis of high aspect-ratio wings using the method of numerical continuation. [Thesis]. Texas A&M University; 2006. Available from: http://hdl.handle.net/1969.1/3846

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


Texas A&M University

25. Lucas, Amy Marie. Gust Load Alleviation for an Aeroelastic System Using Nonlinear Control.

Degree: 2010, Texas A&M University

 The author develops a nonlinear longitudinal model of an aircraft modeled by rigid fuselage, tail, and wing, where the wing is attached to the fuselage… (more)

Subjects/Keywords: Lyapunov Control; Aeroelasticity; Nonlinear Response; Limit Cycle Oscillation; LCO; nonlinear control

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APA (6th Edition):

Lucas, A. M. (2010). Gust Load Alleviation for an Aeroelastic System Using Nonlinear Control. (Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/ETD-TAMU-2009-08-1504

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

Chicago Manual of Style (16th Edition):

Lucas, Amy Marie. “Gust Load Alleviation for an Aeroelastic System Using Nonlinear Control.” 2010. Thesis, Texas A&M University. Accessed February 23, 2020. http://hdl.handle.net/1969.1/ETD-TAMU-2009-08-1504.

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

MLA Handbook (7th Edition):

Lucas, Amy Marie. “Gust Load Alleviation for an Aeroelastic System Using Nonlinear Control.” 2010. Web. 23 Feb 2020.

Vancouver:

Lucas AM. Gust Load Alleviation for an Aeroelastic System Using Nonlinear Control. [Internet] [Thesis]. Texas A&M University; 2010. [cited 2020 Feb 23]. Available from: http://hdl.handle.net/1969.1/ETD-TAMU-2009-08-1504.

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

Council of Science Editors:

Lucas AM. Gust Load Alleviation for an Aeroelastic System Using Nonlinear Control. [Thesis]. Texas A&M University; 2010. Available from: http://hdl.handle.net/1969.1/ETD-TAMU-2009-08-1504

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

26. Elgohary, Tarek Adel Abdelsalam. Nonlinear Analysis of a Two DOF Piecewise Linear Aeroelastic System.

Degree: 2011, Texas A&M University

 The nonlinear dynamic analysis of aeroelastic systems is a topic that has been covered extensively in the literature. The two main sources of nonlinearities in… (more)

Subjects/Keywords: Aeroelasticity; piecewise linear

…for the problem discussing nonlinear aeroelasticity and its effects on flight and its… 

Page 1 Page 2 Page 3 Page 4 Page 5 Page 6 Page 7

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APA (6th Edition):

Elgohary, T. A. A. (2011). Nonlinear Analysis of a Two DOF Piecewise Linear Aeroelastic System. (Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/ETD-TAMU-2010-08-8012

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

Chicago Manual of Style (16th Edition):

Elgohary, Tarek Adel Abdelsalam. “Nonlinear Analysis of a Two DOF Piecewise Linear Aeroelastic System.” 2011. Thesis, Texas A&M University. Accessed February 23, 2020. http://hdl.handle.net/1969.1/ETD-TAMU-2010-08-8012.

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

MLA Handbook (7th Edition):

Elgohary, Tarek Adel Abdelsalam. “Nonlinear Analysis of a Two DOF Piecewise Linear Aeroelastic System.” 2011. Web. 23 Feb 2020.

Vancouver:

Elgohary TAA. Nonlinear Analysis of a Two DOF Piecewise Linear Aeroelastic System. [Internet] [Thesis]. Texas A&M University; 2011. [cited 2020 Feb 23]. Available from: http://hdl.handle.net/1969.1/ETD-TAMU-2010-08-8012.

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

Council of Science Editors:

Elgohary TAA. Nonlinear Analysis of a Two DOF Piecewise Linear Aeroelastic System. [Thesis]. Texas A&M University; 2011. Available from: http://hdl.handle.net/1969.1/ETD-TAMU-2010-08-8012

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


University of Notre Dame

27. Teng Wu. Nonlinear Bluff-Body Aerodynamics</h1>.

Degree: PhD, Civil Engineering and Geological Sciences, 2013, University of Notre Dame

  Wind induced effects on structures governed by the Navier-Stokes equations are not adequately represented by the conventional linear analysis framework. This shortcoming is becoming… (more)

Subjects/Keywords: fluid-structure interaction; reduced-order modeling; bridge; nonlinearity; aerodynamics; aeroelasticity

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APA (6th Edition):

Wu, T. (2013). Nonlinear Bluff-Body Aerodynamics</h1>. (Doctoral Dissertation). University of Notre Dame. Retrieved from https://curate.nd.edu/show/wm117m03w99

Chicago Manual of Style (16th Edition):

Wu, Teng. “Nonlinear Bluff-Body Aerodynamics</h1>.” 2013. Doctoral Dissertation, University of Notre Dame. Accessed February 23, 2020. https://curate.nd.edu/show/wm117m03w99.

MLA Handbook (7th Edition):

Wu, Teng. “Nonlinear Bluff-Body Aerodynamics</h1>.” 2013. Web. 23 Feb 2020.

Vancouver:

Wu T. Nonlinear Bluff-Body Aerodynamics</h1>. [Internet] [Doctoral dissertation]. University of Notre Dame; 2013. [cited 2020 Feb 23]. Available from: https://curate.nd.edu/show/wm117m03w99.

Council of Science Editors:

Wu T. Nonlinear Bluff-Body Aerodynamics</h1>. [Doctoral Dissertation]. University of Notre Dame; 2013. Available from: https://curate.nd.edu/show/wm117m03w99


Miami University

28. Fellows, Mark T. Aeroelastic Stability and Control of Rectangular Plates with Compliant Boundary Supports.

Degree: MS, Computational Science and Engineering, 2014, Miami University

 A proposed design to reduce airframe noise emissions by attaching a flexible fairing between the flap and trailing edge of airplane wings has inspired new… (more)

Subjects/Keywords: Aerospace Engineering; Mechanical Engineering; aeroelasticity; rectangular plate; control; flutter; buckling

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APA (6th Edition):

Fellows, M. T. (2014). Aeroelastic Stability and Control of Rectangular Plates with Compliant Boundary Supports. (Masters Thesis). Miami University. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=miami1407440336

Chicago Manual of Style (16th Edition):

Fellows, Mark T. “Aeroelastic Stability and Control of Rectangular Plates with Compliant Boundary Supports.” 2014. Masters Thesis, Miami University. Accessed February 23, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=miami1407440336.

MLA Handbook (7th Edition):

Fellows, Mark T. “Aeroelastic Stability and Control of Rectangular Plates with Compliant Boundary Supports.” 2014. Web. 23 Feb 2020.

Vancouver:

Fellows MT. Aeroelastic Stability and Control of Rectangular Plates with Compliant Boundary Supports. [Internet] [Masters thesis]. Miami University; 2014. [cited 2020 Feb 23]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=miami1407440336.

Council of Science Editors:

Fellows MT. Aeroelastic Stability and Control of Rectangular Plates with Compliant Boundary Supports. [Masters Thesis]. Miami University; 2014. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=miami1407440336


UCLA

29. Gariffo, James Michael. Generalized Reduced Order Modeling of Aeroservoelastic Systems.

Degree: Mechanical Engineering, 2013, UCLA

 Transonic aeroelastic and aeroservoelastic (ASE) modeling presents a significant technical and computational challenge. Flow fields with a mixture of subsonic and supersonic flow, as well… (more)

Subjects/Keywords: Mechanical engineering; Aerospace engineering; aeroelasticity; aeroservoelasticity; flutter; reduced-order modeling; transonic

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APA (6th Edition):

Gariffo, J. M. (2013). Generalized Reduced Order Modeling of Aeroservoelastic Systems. (Thesis). UCLA. Retrieved from http://www.escholarship.org/uc/item/0rc0c11t

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

Chicago Manual of Style (16th Edition):

Gariffo, James Michael. “Generalized Reduced Order Modeling of Aeroservoelastic Systems.” 2013. Thesis, UCLA. Accessed February 23, 2020. http://www.escholarship.org/uc/item/0rc0c11t.

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

MLA Handbook (7th Edition):

Gariffo, James Michael. “Generalized Reduced Order Modeling of Aeroservoelastic Systems.” 2013. Web. 23 Feb 2020.

Vancouver:

Gariffo JM. Generalized Reduced Order Modeling of Aeroservoelastic Systems. [Internet] [Thesis]. UCLA; 2013. [cited 2020 Feb 23]. Available from: http://www.escholarship.org/uc/item/0rc0c11t.

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

Council of Science Editors:

Gariffo JM. Generalized Reduced Order Modeling of Aeroservoelastic Systems. [Thesis]. UCLA; 2013. Available from: http://www.escholarship.org/uc/item/0rc0c11t

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


University of Victoria

30. Richards, Jenner. An Experimental Investigation of a Joined Wing Aircraft Configuration Using Flexible, Reduced Scale Flight Test Vehicles.

Degree: Department of Mechanical Engineering, 2014, University of Victoria

 The United States Air Force has specified a need for the next generation, High Altitude, Long Endurance aircraft capable of carrying advanced sensor arrays over… (more)

Subjects/Keywords: Aeroelastic; Aeroelasticity; UAV; Joined Wing; SensorCraft; Flight Test; Unmanned Aircraft

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APA (6th Edition):

Richards, J. (2014). An Experimental Investigation of a Joined Wing Aircraft Configuration Using Flexible, Reduced Scale Flight Test Vehicles. (Thesis). University of Victoria. Retrieved from http://hdl.handle.net/1828/5710

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

Chicago Manual of Style (16th Edition):

Richards, Jenner. “An Experimental Investigation of a Joined Wing Aircraft Configuration Using Flexible, Reduced Scale Flight Test Vehicles.” 2014. Thesis, University of Victoria. Accessed February 23, 2020. http://hdl.handle.net/1828/5710.

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

MLA Handbook (7th Edition):

Richards, Jenner. “An Experimental Investigation of a Joined Wing Aircraft Configuration Using Flexible, Reduced Scale Flight Test Vehicles.” 2014. Web. 23 Feb 2020.

Vancouver:

Richards J. An Experimental Investigation of a Joined Wing Aircraft Configuration Using Flexible, Reduced Scale Flight Test Vehicles. [Internet] [Thesis]. University of Victoria; 2014. [cited 2020 Feb 23]. Available from: http://hdl.handle.net/1828/5710.

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

Council of Science Editors:

Richards J. An Experimental Investigation of a Joined Wing Aircraft Configuration Using Flexible, Reduced Scale Flight Test Vehicles. [Thesis]. University of Victoria; 2014. Available from: http://hdl.handle.net/1828/5710

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

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