東華大學圖書館 |

語系: 繁體中文

說明(常見問題)

回圖書館首頁

手機版館藏查詢

登入

回首頁

切換: 標籤 | MARC模式 | ISBD

An Integrated Bi-Fidelity Approach t...

Bieri, Kevin M.

FindBook

Google Book

Amazon

博客來

An Integrated Bi-Fidelity Approach to Parametric Studies of Finite Wing Geometries.

紀錄類型:	書目-電子資源 : Monograph/item
正題名/作者:	An Integrated Bi-Fidelity Approach to Parametric Studies of Finite Wing Geometries./
作者:	Bieri, Kevin M.
出版者:	Ann Arbor : ProQuest Dissertations & Theses, : 2019,
面頁冊數:	156 p.
附註:	Source: Masters Abstracts International, Volume: 81-09.
Contained By:	Masters Abstracts International81-09.
標題:	Aerospace engineering. -
電子資源:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=27662961
ISBN:	9781392540879

An Integrated Bi-Fidelity Approach to Parametric Studies of Finite Wing Geometries.
Bieri, Kevin M.

An Integrated Bi-Fidelity Approach to Parametric Studies of Finite Wing Geometries. - Ann Arbor : ProQuest Dissertations & Theses, 2019 - 156 p.

Source: Masters Abstracts International, Volume: 81-09.

Thesis (M.S.)--University of Colorado at Boulder, 2019.

This item must not be sold to any third party vendors.

An approach to computational fluid dynamics (CFD) studies of the aerodynamic performance of finite wings based on parameter sweeps of the wings' geometries is developed. To reduce computational cost while retaining prediction accuracy, the approach leverages a bi-fidelity surrogate modeling technique which uses the skeletonization of the solution space from a low fidelity model to map a small sample of high fidelity model results throughout the parameter space. To facilitate automatic generation of the discrete realizations of the geometries, a mesh transformation technique integrated into the CFD solver uses linear elastic mesh deformation and mesh improvement post-processing to map a single baseline discretization of the flow problem to each target geometry within the parameter space while preserving the original mesh connectivity and structure in addition to any initial and boundary conditions.The integrated bi-fidelity approach was evaluated by considering the specific application to predicting the sectional lift and drag coefficients distributions for the wing of a medium altitude, long endurance (MALE) unmanned aerial vehicle (UAV) given variations in the wing's span, taper ratio, and sweep angle. Consideration of the mesh transformation technique showed it produced a mesh of a target geometry with a 20% increase in span, a 20% change in taper ratio, and 15° of sweep with comparable quality to both the initial mesh and a mesh manually generated for the target geometry. Consideration of the bi-fidelity technique showed a surrogate model formed with eight high fidelity samples had an average root-mean-square error in its lift prediction relative across eight test cases of 0.5% compared to 14.9% for the low fidelity model alone. The drag prediction of the bi-fidelity model was slightly less accurate due to physics not captured by the high fidelity model but still had a relatively low error of 7.2% compared to 203.5% for the low fidelity model.

ISBN: 9781392540879Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Bi-fidelity

An Integrated Bi-Fidelity Approach to Parametric Studies of Finite Wing Geometries.
LDR:03120nmm a2200373 4500 001 2272942
005 20201105110305.5
008 220629s2019 ||||||||||||||||| ||eng d
020 $a 9781392540879
035 $a (MiAaPQ)AAI27662961
035 $a AAI27662961
040 $a MiAaPQ $c MiAaPQ
100 1 $a Bieri, Kevin M. $3 3550365
245 1 3 $a An Integrated Bi-Fidelity Approach to Parametric Studies of Finite Wing Geometries.
260 1 $a Ann Arbor : $b ProQuest Dissertations & Theses, $c 2019
300 $a 156 p.
500 $a Source: Masters Abstracts International, Volume: 81-09.
500 $a Advisor: Jansen, Kenneth.
502 $a Thesis (M.S.)--University of Colorado at Boulder, 2019.
506 $a This item must not be sold to any third party vendors.
520 $a An approach to computational fluid dynamics (CFD) studies of the aerodynamic performance of finite wings based on parameter sweeps of the wings' geometries is developed. To reduce computational cost while retaining prediction accuracy, the approach leverages a bi-fidelity surrogate modeling technique which uses the skeletonization of the solution space from a low fidelity model to map a small sample of high fidelity model results throughout the parameter space. To facilitate automatic generation of the discrete realizations of the geometries, a mesh transformation technique integrated into the CFD solver uses linear elastic mesh deformation and mesh improvement post-processing to map a single baseline discretization of the flow problem to each target geometry within the parameter space while preserving the original mesh connectivity and structure in addition to any initial and boundary conditions.The integrated bi-fidelity approach was evaluated by considering the specific application to predicting the sectional lift and drag coefficients distributions for the wing of a medium altitude, long endurance (MALE) unmanned aerial vehicle (UAV) given variations in the wing's span, taper ratio, and sweep angle. Consideration of the mesh transformation technique showed it produced a mesh of a target geometry with a 20% increase in span, a 20% change in taper ratio, and 15° of sweep with comparable quality to both the initial mesh and a mesh manually generated for the target geometry. Consideration of the bi-fidelity technique showed a surrogate model formed with eight high fidelity samples had an average root-mean-square error in its lift prediction relative across eight test cases of 0.5% compared to 14.9% for the low fidelity model alone. The drag prediction of the bi-fidelity model was slightly less accurate due to physics not captured by the high fidelity model but still had a relatively low error of 7.2% compared to 203.5% for the low fidelity model.
590 $a School code: 0051.
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Engineering. $3 586835
650 4 $a Fluid mechanics. $3 528155
653 $a Bi-fidelity
653 $a CFD
653 $a Mesh Transformation
653 $a Multi-fidelity
653 $a Surrogate modeling
690 $a 0538
690 $a 0537
690 $a 0204
710 2 $a University of Colorado at Boulder. $b Aerospace Engineering. $3 1030473
773 0 $t Masters Abstracts International $g 81-09.
790 $a 0051
791 $a M.S.
792 $a 2019
793 $a English
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=27662961