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You searched for +publisher:"University of Washington" +contributor:("Bragg, Michael B."). Showing records 1 – 2 of 2 total matches.

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University of Washington

1. Camello, Stephanie Chen. Effect of Ice Accretion Simulation Fidelity on Low-Reynolds Number Swept-Wing Aerodynamic Performance.

Degree: 2017, University of Washington

Understanding how ice accretion affects the aerodynamics of swept-wing aircraft is a vital part of aircraft design, fabrication, and testing. Previous work focused on iced airfoil aerodynamics which did not take into account the geometric complexities of a swept wing. A method to create a series of full-span artificial ice shapes for a swept wing was developed so aerodynamic testing could be performed for a variety of ice shapes. Due to icing scaling limitations and icing wind tunnel size restrictions, ice accretions could not be produced for the full span of a swept wing. Instead, ice was accreted for small sections of the leading edge, laser scanned, and digitally manipulated to manufacture a full-span artificial ice shape. These full-span artificial ice shapes were used in low Reynolds number experimental testing. Wind tunnel testing was performed at Reynolds numbers of 1.8 x 106, 1.6 x 106, and 2.4 x 106 and Mach numbers of 0.09, 0.18, and 0.27, respectively, for model angles of attack ranging from -6 to 16. The swept-wing model used was a scaled version of the NASA Common Research Model wing, which is representative of modern commercial airliner. Force balance, oil-flow visualization, fluorescent mini-tuft visualization, and surface pressure data were collected for 18 leading-edge configurations including 7 high-fidelity ice shapes, 10 low-fidelity versions of these ice shapes, and the clean leading edge without artificial ice shapes present. The goal of this study is to determine how each artificial ice shape configuration affects the aerodynamic performance of the swept-wing model and the role ice shape simulation fidelity plays. Advisors/Committee Members: Bragg, Michael B (advisor).

Subjects/Keywords:

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

APA (6th Edition):

Camello, S. C. (2017). Effect of Ice Accretion Simulation Fidelity on Low-Reynolds Number Swept-Wing Aerodynamic Performance. (Thesis). University of Washington. Retrieved from http://hdl.handle.net/1773/39915

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):

Camello, Stephanie Chen. “Effect of Ice Accretion Simulation Fidelity on Low-Reynolds Number Swept-Wing Aerodynamic Performance.” 2017. Thesis, University of Washington. Accessed January 18, 2019. http://hdl.handle.net/1773/39915.

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

MLA Handbook (7th Edition):

Camello, Stephanie Chen. “Effect of Ice Accretion Simulation Fidelity on Low-Reynolds Number Swept-Wing Aerodynamic Performance.” 2017. Web. 18 Jan 2019.

Vancouver:

Camello SC. Effect of Ice Accretion Simulation Fidelity on Low-Reynolds Number Swept-Wing Aerodynamic Performance. [Internet] [Thesis]. University of Washington; 2017. [cited 2019 Jan 18]. Available from: http://hdl.handle.net/1773/39915.

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

Council of Science Editors:

Camello SC. Effect of Ice Accretion Simulation Fidelity on Low-Reynolds Number Swept-Wing Aerodynamic Performance. [Thesis]. University of Washington; 2017. Available from: http://hdl.handle.net/1773/39915

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


University of Washington

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

Degree: 2018, University of Washington

This thesis studied the aerodynamic effects of a single high-fidelity scalloped ice accretion simulation and a low-fidelity simulation of the same shape. These data were compared to the aerodynamics of a clean 8.9% scale CRM65 semispan wing model at a Reynolds number of 1.6×106. The clean wing experienced an aggressive, tip-first stall and showed a small, strong leading-edge vortex at lower angles-of-attack while the iced cases showed larger, seemingly weaker leading-edge vortices at similar angles. The size of these vortices is larger for the low-fidelity ice shape. The stall pattern for the iced cases was also tip-first, but more gradual than the clean wing. The high-fidelity ice shape produced streamwise flow features over the upper surface of the wing likely due, in part, to flow moving through gaps that exist in the ice shape geometry that disrupted the formation of the leading-edge vortices. These features are thought to change the aerodynamics of the wing by impacting leading-edge vortex formation and delaying flow separation. These gaps do not exist in the low-fidelity shape, where leading-edge vortices are larger, are apparent at lower angles-of-attack, and flow separation occurs earlier over the wing. The low-fidelity scallop ice shape was non-conservative in its aerodynamic performance penalties compared to the full high-fidelity case. Advisors/Committee Members: Bragg, Michael B. (advisor).

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

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

APA (6th Edition):

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

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

Chicago Manual of Style (16th Edition):

Sandhu, Navdeep. “Aerodynamics of a Swept Wing With Simulated Scalloped Ice at Low Reynolds Number.” 2018. Thesis, University of Washington. Accessed January 18, 2019. http://hdl.handle.net/1773/42162.

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

MLA Handbook (7th Edition):

Sandhu, Navdeep. “Aerodynamics of a Swept Wing With Simulated Scalloped Ice at Low Reynolds Number.” 2018. Web. 18 Jan 2019.

Vancouver:

Sandhu N. Aerodynamics of a Swept Wing With Simulated Scalloped Ice at Low Reynolds Number. [Internet] [Thesis]. University of Washington; 2018. [cited 2019 Jan 18]. Available from: http://hdl.handle.net/1773/42162.

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

Council of Science Editors:

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

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

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