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You searched for subject:( flaperon). Showing records 1 – 3 of 3 total matches.

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Brno University of Technology

1. Cejpek, Jakub. Návrh řízeni ultralehkého motorového kluzáku SONG .

Degree: 2011, Brno University of Technology

Cílem této práce je převzít a dále rozvinout typový návrh letounu SONG. Výsledkem bude základní aerodynamický výpočet, návrh příčného řízení včetně pevnostní kontroly vybraných částí. Takto navržený letoun bude připravený pro další výpočty (mechanika letu, pevnost křídla, trupu a ocasních ploch) a pro konkrétnější konstrukční návrh jednotlivých částí letounu.; The objective of this work is to adopt and further expand the type design of the SONG motor glider. The study will result in the basic aerodynamic calculation and the design of lateral control system including structural strength inspection of selected parts. Subsequently, the proposal will allow for further calculation to be made (of flight mechanics, wings strength or fuselage and empennage firmness) and for more specific constructional design of individual components of the glider. Advisors/Committee Members: Mališ, Michal (advisor).

Subjects/Keywords: řízení letounu; flaperon; křidélko; klapka; motorový kluzák; aircraft flight control system; flaperon; aileron; flaps; motor glider

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APA (6th Edition):

Cejpek, J. (2011). Návrh řízeni ultralehkého motorového kluzáku SONG . (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/3886

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):

Cejpek, Jakub. “Návrh řízeni ultralehkého motorového kluzáku SONG .” 2011. Thesis, Brno University of Technology. Accessed August 19, 2019. http://hdl.handle.net/11012/3886.

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

MLA Handbook (7th Edition):

Cejpek, Jakub. “Návrh řízeni ultralehkého motorového kluzáku SONG .” 2011. Web. 19 Aug 2019.

Vancouver:

Cejpek J. Návrh řízeni ultralehkého motorového kluzáku SONG . [Internet] [Thesis]. Brno University of Technology; 2011. [cited 2019 Aug 19]. Available from: http://hdl.handle.net/11012/3886.

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

Council of Science Editors:

Cejpek J. Návrh řízeni ultralehkého motorového kluzáku SONG . [Thesis]. Brno University of Technology; 2011. Available from: http://hdl.handle.net/11012/3886

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


RMIT University

2. Norrison, D. Nomad flutter and flow simulation acceleration for elastic wings.

Degree: 2009, RMIT University

Aircraft are flexible aeroelastic structures. Therefore, in-flight they are susceptible to a self-induced oscillation known as flutter which can lead to rapid and catastrophic structural failure. The aircraft design process must ensure that flutter occurs beyond the flight envelope, yet the Government Aircraft Factories Nomad aircraft has occasionally experienced low speed flutter involving its flaperon. Past attempts to investigate the Nomad’s flaperon flutter were unsuccessful. Consequently, not much is known about the critical flutter mode except that it occurs upon landing at a speed of about 100 knots. The objective of this research was to make a contribution towards the knowledge needed to help resolve the Nomad's flutter. The scope of this work was limited to applying computational methods rather than physical experiments. A nonlinear aeroelastic simulation was deemed necessary for an accurate flutter analysis with the Nomad’s wing geometry in its landing configuration. However, nonlinear aeroelastic methods need significant development in many areas before they can be applied to problems like the Nomad. In particular, the nonlinear aerodynamics component of nonlinear aeroelastic simulations was identified as critical area. Hence, the focus of the research work related to nonlinear computational fluid dynamics (CFD) and more specifically, turbulence modelling, grid generation and the computational cost involved. Flow phenomena around high-lift wings, like the Nomad's, are not well understood under take-off and landing conditions. Therefore, studying the local flowfield structures around the Nomad’s wing-flaperon landing configuration would be valuable. No such examination has been reported in the literature. The steady, two-dimensional flowfield around the Nomad's wing was simulated. Results showed separated regions behind the flaperon and main wing element, and attached flow elsewhere. Pressure distributions along the flaperon were strongly influenced by turbulence model. Thus, existing Reynolds-Averaged Navier–Stokes turbulence models, coupled with wall modelling, are unreliable for this problem. Field grid generation required for nonlinear aerodynamics computations can be laborious and may involve considerable computational resources, especially for moving geometries essential for aeroelastic simulations. Therefore, an efficient grid generation algorithm was developed. It generated a structured O-grid around a single arbitrarily shaped body in two and three dimensions by solving a system of elliptic Laplace or Poisson equations. This algorithm differs from others by implementing several acceleration techniques, including approximate factorisation and the method of false transients, to enhance the convergence rate. Computation times were drastically reduced relative to traditional methods. In nonlinear aeroelastic simulations, over 60% of the total computational time is expended on nonlinear CFD calculations (excluding grid generation). This cost can be reduced by exploiting…

Subjects/Keywords: Fields of Research; Nomad; flaperon; aeroelasticity; high-lift; computational fluid dynamics; turbulence modelling; elliptic grid generation; OpenMP parallelisation; computation acceleration

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

APA (6th Edition):

Norrison, D. (2009). Nomad flutter and flow simulation acceleration for elastic wings. (Thesis). RMIT University. Retrieved from http://researchbank.rmit.edu.au/view/rmit:6164

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):

Norrison, D. “Nomad flutter and flow simulation acceleration for elastic wings.” 2009. Thesis, RMIT University. Accessed August 19, 2019. http://researchbank.rmit.edu.au/view/rmit:6164.

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

MLA Handbook (7th Edition):

Norrison, D. “Nomad flutter and flow simulation acceleration for elastic wings.” 2009. Web. 19 Aug 2019.

Vancouver:

Norrison D. Nomad flutter and flow simulation acceleration for elastic wings. [Internet] [Thesis]. RMIT University; 2009. [cited 2019 Aug 19]. Available from: http://researchbank.rmit.edu.au/view/rmit:6164.

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

Council of Science Editors:

Norrison D. Nomad flutter and flow simulation acceleration for elastic wings. [Thesis]. RMIT University; 2009. Available from: http://researchbank.rmit.edu.au/view/rmit:6164

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


Brno University of Technology

3. Freisleben, Michal. Výpočet zatížení a pevnostní kontrola křídla kluzáku .

Degree: 2009, Brno University of Technology

Tato diplomová práce se zabývá výpočtem zatížení kompozitového křídla a jeho pevnostní kontrolou. Dále obsahuje návrh statické pevnostní zkoušky křídla.; This diploma thesis deals with the calculation of composite wing loading and its stressanalysis. Furthermore work contains design of static strength test wing. Advisors/Committee Members: Jebáček, Ivo (advisor).

Subjects/Keywords: Kompozitové křídlo; pevnostní kontrola; statická pevnostní zkouška; flaperon; kluzák; Composite wing; stress analysis; static strength test; flaperon; glider

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

APA (6th Edition):

Freisleben, M. (2009). Výpočet zatížení a pevnostní kontrola křídla kluzáku . (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/15777

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):

Freisleben, Michal. “Výpočet zatížení a pevnostní kontrola křídla kluzáku .” 2009. Thesis, Brno University of Technology. Accessed August 19, 2019. http://hdl.handle.net/11012/15777.

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

MLA Handbook (7th Edition):

Freisleben, Michal. “Výpočet zatížení a pevnostní kontrola křídla kluzáku .” 2009. Web. 19 Aug 2019.

Vancouver:

Freisleben M. Výpočet zatížení a pevnostní kontrola křídla kluzáku . [Internet] [Thesis]. Brno University of Technology; 2009. [cited 2019 Aug 19]. Available from: http://hdl.handle.net/11012/15777.

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

Council of Science Editors:

Freisleben M. Výpočet zatížení a pevnostní kontrola křídla kluzáku . [Thesis]. Brno University of Technology; 2009. Available from: http://hdl.handle.net/11012/15777

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

.