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RISS 인기검색어
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- 저자 : 임진우(J.W. Yim) (검색결과 3 건)
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천음속 난류 유동장에서의 다중체 항공기 형상의 공력 설계 도구의 개발
이병준(B.J. Lee),이준석(J.S. Lee),임진우(J.W. Yim),김종암(Chongam Kim) 한국전산유체공학회 2007 한국전산유체공학회 학술대회논문집 Vol.2007 No.-
A new design approach for a delicate treatment of complex geometries such as a wing/body configuration is arranged using overset mesh technique under large scale computing environment for turbulent viscous flow. Various pre- and post-processing techniques which are required of overset flow analysis and sensitivity analysis codes are discussed for design optimization problems based on gradient based optimization method (GBOM). The overset flow analysis code is validated by comparing with the experimental data of a wing/body configuration (DLR-F4) from the 1st Drag Prediction Workshop (DPW-Ⅰ). In order to examine the applicability of the present design tools, careful design works for the drag minimization problem of a wing/body configuration are carried out by using the developed aerodynamic shape optimization tools for the viscous flow over multiple-body aircraft geometries.
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Kriging 기반 모델과 매개변수(Adjoint Variable)법을 이용한 항공기형상의 2단계 공력최적설계
임진우(J.W. Yim),이병준(B.J. Lee),김종암(C. Kim) 한국전산유체공학회 2009 한국전산유체공학회 학술대회논문집 Vol.2009 No.4
An efficient and high-fidelity design approach for wing-body shape optimization is presented. Depending on the size of design space and the number of design of variable, aerodynamic shape optimization process is carried out via different optimization strategies at each design stage. In the first stage, global optimization techniques are applied to planform design with a few geometric design variables. In the second stage, local optimization techniques are used for wing surface design with a lot of design variables to maintain a sufficient design space with a high DOF (Degree of Freedom) geometric change. For global optimization, Kriging method in conjunction with Genetic Algorithm (GA) is used. Asearching algorithm of EI (Expected Improvement) points is introduced to enhance the quality of global optimization for the wing-planform design. For local optimization, a discrete adjoint method is adopted. By the successive combination of global and local optimization techniques, drag minimization is performed for a multi-body aircraft configuration while maintaining the baseline lift and the wing weight at the same time. Through the design process, performances of the test models are remarkably improved in comparison with the single stage design approach. The performance of the proposed design framework including wing planform design variables can be efficiently evaluated by the drag decomposition method, which can examine the improvement of various drag components, such as induced drag, wave drag, viscous drag and profile drag.
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크리깅 기반 모델과 매개변수법을 이용한 다중물체의 다단계 형상 최적설계
임진우(J.W. Yim),김종암(C. Kim) 한국전산유체공학회 2011 한국전산유체공학회 학술대회논문집 Vol.2011 No.11
An efficient and high-fidelity design approach for wing-body configuration is presented. Depending on the nature of the design space and the number of design variables, aerodynamic shape optimization is carried out at each design stage via a selective optimization strategy. In the first stage, global optimization techniques are applied to planform design with a few geometric design variables using Genetic Algorithm based on Kriging-EI method. In the second stage, local optimization technique based on discrete adjoint method is employed for wing surface design with numerous design variables which can maintain a sufficient design space with a high DOF (Degree of Freedom) geometric change. By the use of the proposed optimization method, drag minimization is performed in inviscid and viscous flow conditions and the performance of the multi-stage design strategy are compared with the single stage design approach using the drag decomposition method.
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