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Aerodynamic Shape Optimization of a ...

Kuntawala, Nimeesha B.

Aerodynamic Shape Optimization of a Blended-Wing-Body Aircraft Configuration.

紀錄類型:	書目-語言資料,印刷品 : Monograph/item
正題名/作者:	Aerodynamic Shape Optimization of a Blended-Wing-Body Aircraft Configuration./
作者:	Kuntawala, Nimeesha B.
面頁冊數:	112 p.
附註:	Source: Masters Abstracts International, Volume: 50-04, page: 2504.
Contained By:	Masters Abstracts International50-04.
標題:	Engineering, Aerospace. -
電子資源:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=MR76792
ISBN:	9780494767924

Aerodynamic Shape Optimization of a Blended-Wing-Body Aircraft Configuration.
Kuntawala, Nimeesha B.

Aerodynamic Shape Optimization of a Blended-Wing-Body Aircraft Configuration. - 112 p.

Source: Masters Abstracts International, Volume: 50-04, page: 2504.

Thesis (M.A.Sc.)--University of Toronto (Canada), 2011.

Increasing environmental concerns and fuel prices motivate the study of alternative, unconventional aircraft configurations. One such example is the blended-wing-body configuration, which has been shown to have several advantages over the conventional tube- and-wing aircraft configuration. In this thesis, a blended-wing-body aircraft is studied and optimized aerodynamically using a high-fidelity Euler-based flow solver, integrated geometry parameterization and mesh movement, adjoint-based gradient evaluation, and a sequential quadratic programming algorithm. Specifically, the aircraft is optimized at transonic conditions to minimize the sum of induced and wave drag. These optimizations are carried out with both fixed and varying airfoil sections. With varying airfoil sections and increased freedom, up to 52% drag reduction relative to the baseline geometry was achieved: at the target CL of 0.357, a CD of 0.01313 and an inviscid lift-to-drag ratio of 27.2 were obtained.

ISBN: 9780494767924Subjects--Topical Terms:

845476
Engineering, Aerospace.

Aerodynamic Shape Optimization of a Blended-Wing-Body Aircraft Configuration.
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245 1 0 $a Aerodynamic Shape Optimization of a Blended-Wing-Body Aircraft Configuration.
300 $a 112 p.
500 $a Source: Masters Abstracts International, Volume: 50-04, page: 2504.
500 $a Adviser: David W. Zingg.
502 $a Thesis (M.A.Sc.)--University of Toronto (Canada), 2011.
520 $a Increasing environmental concerns and fuel prices motivate the study of alternative, unconventional aircraft configurations. One such example is the blended-wing-body configuration, which has been shown to have several advantages over the conventional tube- and-wing aircraft configuration. In this thesis, a blended-wing-body aircraft is studied and optimized aerodynamically using a high-fidelity Euler-based flow solver, integrated geometry parameterization and mesh movement, adjoint-based gradient evaluation, and a sequential quadratic programming algorithm. Specifically, the aircraft is optimized at transonic conditions to minimize the sum of induced and wave drag. These optimizations are carried out with both fixed and varying airfoil sections. With varying airfoil sections and increased freedom, up to 52% drag reduction relative to the baseline geometry was achieved: at the target CL of 0.357, a CD of 0.01313 and an inviscid lift-to-drag ratio of 27.2 were obtained.
590 $a School code: 0779.
650 4 $a Engineering, Aerospace. $3 845476
690 $a 0538
710 2 $a University of Toronto (Canada). $b Aerospace Science and Engineering. $3 845686
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790 1 0 $a Zingg, David W., $e advisor
790 $a 0779
791 $a M.A.Sc.
792 $a 2011
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=MR76792

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