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Aerodynamic Shape Optimization using Overset Mesh Technique for Multiple Body Aircraft Geometries

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dc.contributor.authorLee, Byung Joon-
dc.contributor.authorYim, Jin Woo-
dc.contributor.authorYoon, Sung-Hwan-
dc.contributor.authorKim, Chongam-
dc.date.accessioned2009-08-07T03:36:18Z-
dc.date.available2009-08-07T03:36:18Z-
dc.date.issued2007-05-
dc.identifier.citationThe 7th World Congress on Structural and Multidisciplinary Optimization, COEX Seoul, 21 May - 25 May 2007, Koreaen
dc.identifier.urihttps://hdl.handle.net/10371/6495-
dc.description.abstractA new design approach for a delicate treatment of complex geometries such as wing/body configuration is arranged using overset mesh technique under large scale computing environment. For the in-depth study of the flow physics and highly accurate design, several special overlapped structured blocks such as collar grid, tip-cap grid, and etc. which are commonly used in refined drag prediction are adopted to consider the applicability of the design code to practical problems. Various pre- and post-processing techniques for overset flow analysis and sensitivity analysis are devised or implemented to adapt overset mesh technique to the design optimization problem based on Gradient Based Optimization Method (GBOM). In the pre-processing, the convergence characteristics of the flow solver and sensitivity analysis are improved by overlap optimization method. Moreover, a new post-processing method, Spline-Boundary Intersecting Grid (S-BIG) scheme, is proposed by considering the ratio of cell area for more refined prediction of aerodynamic coefficients and convenient evaluation of sensitivities under parallel computing environment. For the sensitivity analysis, adjoint formulations for overset boundary conditions are implemented into the fully hand-differentiated sensitivity analysis code. A smooth geometric modification on the overlapped surface boundaries and evaluation of grid sensitivities can be performed by mapping from planform coordinate to the surface meshes with Hicks-Henne function. Careful design works for the drag minimization problem of a transonic wing and a wing/body configuration are performed using the newly-developed and -applied overset mesh techniques. And the design results from conventional design problem demonstrate the capability of the present design approach successfully.en
dc.description.sponsorshipThe authors appreciate financial support by the Brain Korea-21 Project for the Mechanical and Aerospace Engineering
Research at Seoul National University and by the Korea Science and Engineering Foundation (Grant R01-2005-000-10059-0).
en
dc.language.isoenen
dc.subjectDiscrete Adjoint Variable Methoden
dc.subjectOverset Approachen
dc.subjectOptimal Shape Designen
dc.subjectS-BIG(Spline-Boundary Intersecting Grid)en
dc.subjectComplex Geometryen
dc.titleAerodynamic Shape Optimization using Overset Mesh Technique for Multiple Body Aircraft Geometriesen
dc.typeConference Paperen
dc.contributor.AlternativeAuthor이병준-
dc.contributor.AlternativeAuthor임진우-
dc.contributor.AlternativeAuthor윤성환-
dc.contributor.AlternativeAuthor김종암-
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College of Engineering/Engineering Practice School (공과대학/대학원)Dept. of Mechanical Aerospace Engineering (기계항공공학부)Others_기계항공공학부
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