• 대한조선학회논문집
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• 제44권1호
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• pp.8-15
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• 2007

In this paper, numerical calculations are performed to analyze the unsteady flow of NACA airfoil sections. In order to ease the flow computation for the fluid region changing in time, improve the quality of solution and simplify the grid generation for the oscillating foil flow, the computational method adopts a moving and deforming mesh with the multi-block grid topology. The multi-block, structured-unstructured hybrid grid is generated using the commercial meshing software Gridgen V15. The MDM (Moving & Deforming Mesh) and the UDF (User Define function) function of FLUENT 6 are adopted for computing turbulent flows of the foil in pitching motion. Computed unsteady lift and drag forces are compared with experimental data. in general, the characteristics of unsteady lift and drag of the experiments are reproduced well in the numerical analysis.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2005년도 창립60주년 기념 추계 학술대회
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• pp.85.1-85.1
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• 2005

• 정보과학회 논문지
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• 제44권6호
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• pp.613-620
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• 2017

스카이라인 질의는 사용자들의 다양한 기준을 만족하는 데이터를 찾기 때문에 의사 결정 문제 등에서 폭넓게 사용되고 있다. 최근의 스카이라인 질의는 대용량 데이터베이스 처리를 위해 맵리듀스 프레임워크를 사용하는 연구들이 많이 진행되었으며 특히 맵리듀스에 기존의 색인 구조를 적용하는 방식으로 연구가 활발히 진행되고 있다. 스카이라인의 특징 중 하나는 원점에서 가까운 데이터일수록 더 많은 영역을 지배한다는 점이다. 하지만 기존의 색인 구조는 이와 같은 스카이라인의 특징을 반영하지 못하는 단점이 있었다. 본 논문에서는 그리드의 셀들을 스카이라인의 특징을 고려하여 묶는 그리드 블록 구조와 원점과 가까운 데이터가 없을 때도 사용 가능한 2계층 그리드 블록 구조, 그리고 2계층 그리드 블록 구조를 사용한 효율적인 스카이라인 질의 기법을 제안하였다.

• International Journal of Aeronautical and Space Sciences
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• 제1권1호
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• pp.13-20
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• 2000

The applications of CFD in the design process of a transonic civil transport at Korea Aerospace Research Institute (KARI) are outlined. Three Navier-Stokes solvers, developed at KARI with different grid approaches, are used to predict the aerodynamic coefficients and solve the flowfield of various configurations. Multi-block, Chimera, and unstructured grids are the approaches implemented. The accuracy of the codes is verified for the transonic flow about RAE wing/fuselage configuration. The multi-block code is used to provide the detailed data on the flowfield around a wall interference model with different test section sizes which will be used in establishing the wall interference correction method. The subsonic and transonic flowfields about K100-04A, one of the configurations of a 100-seater transport developed by KARI and Korea Commercial Aircraft Development Consortium (KCDC), are computed to predict the aerodynamic coefficients. The results for the subsonic flow are compared with those of wind tunnel test, and the agreement is found to be excellent. The interference effect of nacelle installation on the wing of K100-04A is also investigated using the unstructured grid method, and about 10% reduction in wing lift is observed. The accuracy of the three developed codes is verified, and they are used as an efficient tool in the design process of a transonic transport.

• 대한조선학회논문집
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• 제42권6호
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• pp.583-592
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• 2005

The turbulent free surface flow around a self-propelled KRISO 138K LNG Carrier is numerically simulated using the finite volume based multi-block RANS code, WAVIS developed at HRISO. The realizable k-$\varepsilon$ turbulence model with a wail function is employed for the turbulence closure. The free surface is captured with the Level-Set method and body forces are used to model the effects of a propeller without resolving the detail blade flow. In order to obtain an accurate free surface solution and stable convergence, the computations are executed with a proper fine grid refinement around the free surface and with an adoption of implicit discretization scheme for the Level-Set formulation. The computed velocity vectors at the several stations and wave patterns show a good agreement with the experimental results measured at the KRISO towing tank.

• 대한조선학회논문집
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• 제40권5호
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• pp.36-42
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• 2003

A CFD simulation technique has been developed to handle the unsteady body motion with large amplitude by use of overlapping multi-block grid system. The three-dimensional, viscous and incompressible flow around body is investigated by solving the Navier-Stokes equations, and the motion of body is represented by moving effect of the grid system. Composite grid system is employed in order to deal with both the body motion with large amplitude and the condition of numerical wave maker in convenience at the same time. The governing equations, Navier-Stokes (N-S) and continuity equations, are discretized by a finite volume method, in the framework of an O-H type boundary-fitted grid system (inner grid system including test model) and a rectangular grid system (outer grid system including simulation equipments for generation of wave environments). If this study, several flow configurations, such as an oscillating cylinder with large KC number, are studied in order to predict and evaluate the hydrodynamic forces. Furthermore, the motion simulation of a Series 60 model advancing in a uniform flow under the condition of enforced roll motion of angle 20$^{\circ}$ is performed in the developed numerical wave tank.

• 한국항공우주학회지
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• 제35권8호
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• pp.661-669
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• 2007

지면효과에 대한 수치해석을 위한 격자생성 과정에서 발생하는 어려움을 해소하기 위하여 중첩격자 기법을 이용한 수치해석 기법의 타당성에 대한 연구를 수행하고 그 신뢰성을 검증하였다. 지면효과가 있는 경우와 없는 경우 RAE 101 익형주위의 저속 난류 유동장에 대한 수치해석을 수행하였고 다중블록격자 기법과 중첩격자 기법을 적용한 수치해석 결과를 실험결과와 비교하였다. 이를 통하여 중첩격자 기법을 이용함으로써 지면효과에 대한 수치해석과정을 정확하고 격자생성 문제없이 효과적으로 수행할 수 있음을 보였다.

• 인터넷정보학회논문지
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• 제11권2호
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• pp.49-60
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• 2010

H.264/AVC 표준은 여러 가지 신기술들을 접목시킴으로써 기존의 동영상 표준들보다 한층 개선된 부호화 효율성을 제공한다.하지만, H.264/AVC 인코더의 향상된 부호화 기술은 그것의 전반적인 복잡도를 크게 증가시켰다. 따라서, 인코더의 복잡도 수준을 경감시키기 위한 최적화의 연구는 중대한 선결 과제이다. 특히, 움직임 추정 부분에 대한 계산량의 비율은 인코더의 작업시간을 크게 좌우한다. 본 논문에서는 완전 다이아몬드와 12각형을 기본 탐색 패턴으로 사용하고 특정한 임계기준치를 적용시킴으로써 효율적으로 정적 블록들을 스킵하는 다이아몬드 웹 격자 탐색 알고리즘을 제안한다. 실험 결과는 본 논문에서 제안된 기법이 기존의 UMHexagonS 알고리즘의 계산량을 12%까지 감소시키면서도 유사한 PSNR을 유지한다는 것을 보여준다.

• 정보통신설비학회논문지
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• 제10권2호
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• pp.53-61
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• 2011

This research presents an adaptive fast motion estimation (ME) computation on the stage of uneven multi-hexagon grid search (UMHGS) algorithm included in an unsymmetrical-cross multi-hexagon-grid search (UMHexagonS) in H.264 standard. The proposed adaptive method is based on statistical analysis and previously obtained motion vectors to reduce the computational complexity of ME. For this purpose, the algorithm is decomposed into three processes: skipping, terminating, and reducing search areas. Skipping and terminating are determined by the statistical analysis of the collected minimum SAD (sum of absolute difference) and the search area is constrained by the slope of previously obtained motion vectors. Simulation results show that 13%-23% of ME time can be reduced compared with UMHexagonS, while still maintaining a reasonable PSNR (peak signal-to-noise ratio) and average bitrates.

• 한국전산유체공학회지
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• 제2권2호
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• pp.51-58
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• 1997

A reliable computational solver has been developed for the analysis of three-dimensional inviscid compressible flows around a nacelle of a high bypass ratio turbofan engine, The numerical algorithm is based on the modified Godunov scheme to allow the second order accuracy for space variables, while keeping the monotone features. Two step time integration is used not only to remove time step limitation but also to provide the second order accuracy in a time variable. The multi-block approach is employed to calculate the complex flow field, using an algebraic, conformal, and elliptic method. The exact solution of Riemann problem is used to define boundary conditions. The accuracy of the developed solver is validated by comparing its results around the isolated nacelle in the cruise flight regime with the solution obtained using a commercial code "RAMPANT. "