• International Journal of Aeronautical and Space Sciences
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• 제10권1호
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• pp.104-111
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• 2009

An unstructured overset mesh method has been developed for the simulation of unsteady flow fields around isolated rotors and rotor-fuselage configurations. The flow solver was parallelized for the efficient calculation of complicated flows requiring a large number of cells. A quasi-unsteady mesh adaptation technique was adopted to enhance the spatial accuracy of the solution and to better resolve the rotor wake. The method has been applied to calculate the flow fields around rotor-alone and rotor-fuselage configurations in forward flight. Validations were made by comparing the predicted results with those of measurements. It was demonstrated that the present method is efficient and robust for the prediction of unsteady time-accurate flow fields involving multiple bodies in relative motion.

• 한국CDE학회논문집
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• 제18권6호
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• pp.461-469
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• 2013

Computer simulation with FEM is very useful to analyze hypervelocity impact phenomena that are tremendously expensive or otherwise too impractical to analyze experimentally. Shock physics can be efficiently handled by mesh adaptation which allows finite element mesh to be locally optimized to resolve moving shock wave in explosion. In this paper, an adaptive meshing technique based upon quadtree data structure was applied to resolve ballistic impact phenomena. The technique can adaptively refine a mesh in the neighborhood of a shock and coarsen the mesh for the smooth flow behind the shock according to a criterion. The criterion for refinement and coarsening is based upon the standard deviation of the gradient of shock pressure on the associated field. Shock simulation starts with the rough mesh of the pressure field and mesh density is increased locally under the criterion at each time step. The results show that the mesh adaptation enables to minimize the global computation error of FEM and to increase storage and computational saving compared to the fixed resolution of the conventional static mesh approach.

• International Journal of Aeronautical and Space Sciences
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• 제18권4호
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• pp.601-613
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• 2017

An adjoint-based error estimation and mesh adaptation study is conducted for two-dimensional viscous flows on unstructured hybrid meshes. The error in an integral output functional of interest is estimated by a dot product of the residual vector and adjoint variable vector. Regions for the mesh to be adapted are selected based on the amount of local error at each nodal point. Triangular cells in the adaptive regions are refined by regular refinement, and quadrangular cells near viscous walls are bisected accordingly. The present procedure is applied to single-element airfoils such as the RAE2822 at a transonic regime and a diamond-shaped airfoil at a supersonic regime. Then the 30P30N multi-element airfoil at a low subsonic regime with a high incidence angle (${\alpha}=21deg.$) is analyzed. The same level of prediction accuracy for lift and drag is achieved with much less mesh points than the uniform mesh refinement approach. The detailed procedure of the adjoint-based mesh refinement for the multi-element airfoil case show that the basic flow features around the airfoil should be resolved so that the adjoint method can accurately estimate an output error.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2011년 춘계학술대회논문집
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• pp.294-301
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• 2011

A two-dimensional hybrid flaw solver has been developed for the accurate and efficient simulation of steady and unsteady flaw fields. The flow solver was cast to accommodate two different topologies of computational meshes. Triangular meshes are adopted in the near-body region such that complex geometric configurations can be easily modeled, while adaptive Cartesian meshes are, utilized in the off-body region to resolve the flaw more accurately with less numerical dissipation by adopting a spatially high-order accurate scheme and solution-adaptive mesh refinement technique. A chimera mesh technique has been employed to link the two flow regimes adopting each mesh topology. Validations were made for the unsteady inviscid vol1ex convection am the unsteady turbulent flaws over an NACA0012 airfoil, and the results were compared with experimental and other computational results.

• 한국항공우주학회지
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• 제33권2호
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• pp.11-21
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• 2005

3차원 비정렬 격자를 이용한 로터-동체 공력 상호작용에 대한 수치적 해석을 수행하였다. 로터와 동체간의 상대적인 운동을 모사하기 위하여 해석 유동장을 회전하는 부분과 정지된 부분으로 나누어 계산하였다. 블레이드 끝단에서 생성되는 끝단 와류를 포착하기 위하여 준 비정상 적응 격자 기법을 도입하였다. 또한 낮은 속도로 전진 비행하는 헬리콥터 해석을 위해서 저 마하수 예조건화 기법을 적용하였다. 로터-동체 공력 간섭현상에 대한 검증을 위해 Georgia Tech 형상과 NASA에서 실험한 ROBIN 형상에 대한 실험 결과와 비교하여 본 연구 해석 기법이 타당함을 보였다.

• 한국통신학회:학술대회논문집
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• 한국통신학회 2006년도 하계종합학술발표회 논문 초록집
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• pp.387-387
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• 2006

• 한국통신학회논문지
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• 제32권1B호
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• pp.1-10
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• 2007

논문에서는 인터넷 트래픽 환경에서 예측하기 어려운 동적 트래픽은 물론 양방향 비대칭적 트래픽을 광 네트워킹 기술을 이용하여, WDM(Wavelength Division Multiplexing) Mesh 네트워크로 수용하는 방안을 제안한다. 제안된 방안에서는 중간 노드(intermediate node)에서 변동하는 인터넷 트래픽에 대한 IP 라우터의 스위칭 통계정보를 기반으로 새로운 광경로를 결정하도록 함으로써, 네트워크의 동적인 그리고 분산적인 트래픽 제어가 이루어지도록 하였다. 이로써 인터넷 트래픽의 실시간적 변동에 따른 RWA(Routing and Wavelength Assignment)의 효율성 열화 효과를 줄이면서 네트워크의 확장성과 유연성이 개선되도록 하였다. 본 논문에서는 노드에서의 트래픽 형상 분석방법과 광경로 설정/절체 과정에 대해 설명하고, 컴퓨터 시뮬레이션을 통해 제안한 개념의 성능을 분석하였다.

• 한국항공우주학회지
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• 제30권2호
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• pp.1-11
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• 2002

본 연구에서는 특별히 PC cluster와 같은 병렬 환경에서 효율적인 계산을 수행할 수 있는 격자중심에 기초한 직접모사 기법을 개발하였다. 병렬환경 하에서의 효과적인 계산 수행을 위해서는 전체 계산 영역을 격자수와 각 격자에 할당되는 모사 입자 수를 고려한 부 영역들로 나누어주었다. 또한, 격자 사용의 효율성 증대를 위해서는 매우 성긴 격자에서부터 출발하여 점차적인 격자 적응을 수행하였다. 본 방법은 2차원의 초음속 평판 문제와 축대칭의 Rothe, 노즐 문제에 적용하였다. 그 결과로부터 본 방법을 사용하면 기존의 입자 중심 기법에 비해 매우 효율적으로 희박기체 유동을 해석할 수 있음을 알 수 있었다.

• 수산해양교육연구
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• 제25권4호
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• pp.928-936
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• 2013

This thesis is the fundamental study on the adaptation of escape device for reducing small fishes in set-net. The escape devices for experiments were made the mesh-type devices with three different mesh sizes (60.6, 75.8 and 120.0mm). The experiments of size selectivity on escape devices were conducted by using two kinds of species as black rockfish (Sebastes schlegeli) and sea perch (Lateolabrax maculatusi) in the experimental tank. The size selectivity curve was fitted by using a logistic function and the parameters of selectivity curve were estimated by a maximum likelihood method. In the results; 50% selection ranges for the mesh-type escape devices with three different mesh sizes were; a black rockfish was 18.99 in mesh size 60.6mm and 21.96 in mesh size 75.8mm (120mm could not estimate). A sea perch was 22.02 in mesh 60.6mm and 24.46 in mesh size 75.8mm (120mm could not estimate). The 50% selection range of a black rockfish was wilder than a sea perch about 1.1~.2 time. Therefore, the small fishes are able to reduce by using the mesh type escape device. However, the optimum mesh size should be decided to consider the size of target species and economics of catches.

• 한국자동차공학회논문집
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• 제4권4호
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• pp.179-189
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• 1996

An unstructured grid finite-volume method has been applied to predict the linear and nonlinear attenuation characteristics of the expansion chamber silencer system. In order to achieve a grid flexibility and a solution adaptation for geometrically silencer system. In order to achieve a grid flexibility and a solution adaptation for geometrically complex flow regions associated with the actual silencers, the unstructured mesh algorithm in context with the node-centered finite volume method has been employed. The present numerical model has been validated by comparison with the analytical solutions and the experimental data for the acoustic field of the concentric expansion chamber with and without pulsating flows, as well as the axisymmetric blast flowfield with open end. Effects of the chamber geometry on the nonlinear wave attenuation characteristics is discussed in detail.