• 한국전산유체공학회지
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• 제17권4호
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• pp.56-68
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• 2012

Nowadays, Unmanned Combat Air Vehicle(UCAV) has become an important aircraft system for the national defense. For its efficiency and survivability, shape optimization of UCAV is an essential part of its design process. In this paper, shape optimization of UCAV was processed for aerodynamic performance improvement and Radar Cross Section(RCS) reduction using Multi Objective Genetic Algorithm(MOGA). Lift and induced drag, friction drag, RCS were calculated using panel method, boundary layer theory, Physical Optics(PO) approximation respectively. In particular, calculation applied Radar Absorbing Material(RAM) was performed for the additional RCS reduction. Results are indicated that shape optimization is performed well for improving aerodynamic performance, reducing RCS. Further study will be performed with higher fidelity tools and consider other design segments including structure.

• 한국철도학회논문집
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• 제18권4호
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• pp.279-288
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• 2015

다양한 3차원 전두부 형상을 효과적으로 모델링할 수 있는 열차형상함수를 이용하여 실제 차량인 KTX 산천 전두부 형상의 공기저항을 저감하는 최적설계를 수행하였다. KTX 산천 전두부의 2차원 단면형상의 특성 곡선을 추출하고 열차형상함수를 이용하여 KTX 산천의 최적설계용 유선형 기본형상을 구성하였다. 기본형상을 이용해 상용 고속열차 전두부의 형상 제약조건을 위반하지 않는 설계공간을 구축하였다. Broyden-Fletcher-Goldfarb-Shanno 알고리즘을 이용한 최적설계를 수행하여 기본형상 대비 약 6%의 공기저항을 저감할 수 있었다. 최적형상은 기본형상에 비해 전두부 길이가 길고 끝단이 약간 날카로운 형상을 가져 후미차량에서의 와류의 크기를 줄임으로써 공기저항을 저감하였다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2008년도 춘계학술대회논문집
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• pp.130-133
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• 2008

In this paper the trust region method is studied and applied in aerodynamic shape optimization. The trust region method is a gradient-based optimization method, but it is not as popular as other methods in engineering computations. Its theory will be explained for unconstrained optimization problems and a trust region subproblem will be solved with the dogleg method. After verifying the trust region method with analytical test problems, it is applied to aerodynamic shape design optimization and the performance of airfoil is improved successfully.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2004년도 추계 학술대회논문집
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• pp.187-191
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• 2004

The conventional reliability based design optimization(RBDO) methods require high computational cost compared with the deterministic design optimization(DO) methods. To overcome the computational inefficiency of RBDO, single loop methods have been proposed. These need less function calls than that of RBDO but much more than that of DO. In this study, the approximate reliability method is proposed that the computational requirement is nearly the same as DO and the reliability accuracy is good compared with that of RBDO. Using this method, the 3-D viscous aerodynamic shape design optimization with uncertainty is performed very efficiently.

• 한국철도학회:학술대회논문집
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• 한국철도학회 2000년도 추계학술대회 논문집
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• pp.499-505
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• 2000

The shape of the KHST, and of the power car in particular, is largely determined by aerodynamic considerations. At high speeds, air resistance accounts for the major part of overall resistance to forward motion. Further points to be considered are environmentally undesirable acoustic phenomena and pressure waves. Minimizing power requirements and environmentally-unfriendly noise and pressure waves are thus major objectives in the development of the KHST. When deciding on the aerodynamic design of the power car, the entire train set has to be taken into consideration. This paper describes the design process and results about the front shape of the KHST.

• 한국철도학회:학술대회논문집
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• 한국철도학회 1999년도 추계학술대회 논문집
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• pp.115-120
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• 1999

The shape of the KHST, and of the power car in particular. is largely determined by aerodynamic considerations. At high speeds, air resistance accounts for the major part of overall resistance to forward motion. Further points to be considered are environmentally undesirable acoustic phenomena and pressure waves. Minimizing power requirements and environmentally-unfriendly noise and pressure waves are thus major objectives in the development of the KHST. When deciding on the aerodynamic design of the power car, the entire train set has to be taken into consideration. This paper describes the design process and results about the front shape of the KHST.

• 국제초고층학회논문집
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• 제12권4호
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• pp.287-297
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• 2023

This paper briefly discusses current issues in wind engineering, including the enhancement of aerodynamic database and AI-assisted design, aerodynamic characteristics of tall buildings with atypical building shapes, application of computation fluid dynamics to wind engineering, evaluation of aerodynamic force coefficients based on a probabilistic method, estimation of tornadic wind speed (JEF scale) and effect of the Ekman Spiral on tall buildings.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2005년도 춘계 학술대회논문집
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• pp.191-196
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• 2005

For the improvement of aerodynamic performance of the turbine blade in a turbopump for the liquid rocket engine, the optimization of turbine profile shape has been studied. The turbine in a turbopump in this study is a partial admission of impulse type, which has twelve nozzles and supersonic inflow. Due to the separated nozzles and supersonic expansion, the flow field becomes complicates and shows oblique shocks and flow separation. To increase the blade power, redesign of the blade shape using CFD and optimization method was attempted. The turbine cascade shape was represented by four design parameters. For optimization, genetic algorithm based upon non-gradient search has been selected as a optimizer. As a result, the final blade has about 4 percent more blade power than the initial shape.

• 한국전산유체공학회지
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• 제10권2호
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• pp.54-59
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• 2005

For the improvement of aerodynamic performance of the turbine blade in a turbopump for the liquid rocket engine, the optimization of turbine profile shape has been studied. The turbine in a turbopump in this study is a partial admission of impulse type, which has twelve nozzles and supersonic inflow. Due to the separated nozzles and supersonic expansion, the flow field becomes complicate and shows oblique shocks and flow separation. To increase the blade power, redesign ol the blade shape using CFD and optimization methods was attempted. The turbine cascade shape was represented by four design parameters. For optimization, a genetic algorithm based upon non-gradient search hue been selected as an optimizer. As a result, the final blade has about 4 percent more blade power than the initial shape.

• 한국산학기술학회논문지
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• 제18권12호
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• pp.9-16
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• 2017

본 논문에서는 풍력 발전기 블레이드 공력 설계 프로세스를 정립하고, 최적화 설계 전략을 제시 하였으며, 공력 설계 진행시에 반드시 검토 필요한 제약 조건들에 대해서 정리 하였다. 이를 토대로 하여 연구 목적뿐 아니라, 블레이드 설계자가 실제 업무에 쉽게 적용 가능하고, 초기 개념설계 단계부터 최종 3차원 형상 상세 설계 단계까지 통합적으로 수행이 가능한 BEMT 기반의 공력 설계 프로그램을 개발하였다. 개발된 프로그램 AeroDA는 개념 설계 모듈, 기본 설계 모듈, 최적 TSR 도출 모듈, 국부 형상 최적화 모듈, 성능 해석 모듈, 설계 검증 모듈 및 3차원 형상생성 모듈로 구성이 된다. 개발된 프로그램을 활용하여 NREL에서 공개 배포한 5MW 블레이드를 기반으로하여 하중저감을 위한 개선 설계를 진행하여 본 프로그램이 최적화 설계에 유용하게 사용 가능함을 확인 하였다. 또한 10kW 블레이드 공력 설계 및 터빈 상세 성능 해석을 진행하고, 이를 상용 전문 프로그램 DNV GL Bladed 결과와 비교하여 정확도를 검증하였다.