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RISS 인기검색어
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- 주제어 : 파섹(PARSEC) (검색결과 3 건)
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모멘트 기법과 PARSEC 함수를 이용한 에어포일 신뢰성 기반 최적설계
이재훈(Jae Hun Lee),강희엽(Hee Youb Kang),권장혁(Jang Hyuk Kwon),곽병만(Byung Man Kwak) 한국전산유체공학회 2010 한국전산유체공학회 학술대회논문집 Vol.2010 No.5
In this study, reliability-based design optimizations of airfoils were performed. PARSEC function was used to consider the uncertainty of the aerodynamic shape for the reliability-based shape optimization of airfoils. Among various reliability analysis methods, the moment method was used to compute the probability of failure of the aerodynamic performance. The accuracy of the reliability analysis was compared with other method and it was found that the moment method predicts the probability accurately. Deterministic and reliability-based optimizations were performed for the shape of the RAE2822 airfoil and it was demonstrated that reliability-based optimum assures the aerodynamic performances under uncertainties of the shape of the airfoil.
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모멘트 기법과 PARSEC 함수를 이용한 에어포일 신뢰성 기반 최적설계
이재훈(J. Lee),강희엽(H. Kang),권장혁(J. Kwon),곽병만(B. Kwak),정경진(K. Jung) 한국전산유체공학회 2012 한국전산유체공학회지 Vol.17 No.2
In this study, the reliability-based design optimization of the airfoil was performed. PARSEC function was used to consider the uncertainty of the aerodynamic shape for the reliability-based shape optimization of airfoils. Among various reliability analysis methods, the moment method was used to compute the probability of failure of the aerodynamic performance. The accuracy of the reliability analysis was compared with other methods and it was found that the moment method predicts the probability of failure accurately. Deterministic and reliability-based optimizations were performed for the shape of the airfoil and it was demonstrated that reliability-based optimum assures the aerodynamic performances under uncertainties of the shape of the airfoil.
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실수기반 다목적 적응영역 유전자 알고리즘과 자가조직도를 이용한 익형 형상 설계 연구
정성기(S.K. Jung),김지홍(J.H. Kim) 한국전산유체공학회 2013 한국전산유체공학회 학술대회논문집 Vol.2013 No.5
An engineering design needs many trade-off studies and an analysis for interrelationship among design parameters to simultaneously fulfil various requirements. Further, in modern aircraft designs, the multi-objective optimization problem is emerged to meet the maximum lift, lift-to-drag ratio and others. Moreover a parameter-based investigation for performance improvement is essential to satisfy further requirements. As this purpose, the Adaptive Range Multi-Objective Genetic Algorithm code was developed, and an interrelationship among design parameters Is analyzed using the Self-Organizing Map. In order to achieve the better maximum lift and lift-to-drag ratio than reference airfoil at landing and cruise conditions, maximum lift coefficient and lift-to-drag ratio were chosen as object functions. Furthermore, the PARSEC method reflecting geometrical properties of airfoil was adopted to generate airfoil shapes. Finally, two airfoils, which show better aerodynamic performance that a reference airfoil, were chosen. as a result, maximum lift coefficient and lift-to-drag ratio were increased of 3.32% and 2.26% for first candidate airfoil and 2.48% and 1.69% for second candidate airfoil. Also interrelationship among design parameters for all candidates is analyzed using the Self-Organizing Map.
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