• 한국컴퓨터그래픽스학회논문지
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• 제15권1호
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• pp.1-6
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• 2009

이 논문은 비격자메쉬에서의 비물리적 감쇄현상을 감소시키는 새로운 CIP 대류방법을 제안한다. 제시되는 방법은 물리량과 물리량의 미분정보를 함께 사용하여 기존의 선형방법보다 더 정확한 물리현상을 반영할 수 있다. 비격자메쉬에서 해결하기 힘든 CIP의 비대류항을 풀기 위해 기존의 격자 메쉬에서 사용되었던 유한차분법 방법과는 다른 유한체적법을 사용하였다. 그리고 대류항의 보다 나은 정확도를 위해 여러가지 보간법에 대해 정확도 실험을 수행하였으며, 선형방법과의 비교 실험을 통해 보다 적은 비물리적 감쇄현상을 보임을 확인할 수 있었다.

• International Journal of Aeronautical and Space Sciences
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• 제12권2호
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• pp.190-199
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• 2011

Unsteady flow simulations of complete helicopter configurations were conducted, and the flow fields and the aerodynamic interferences between the main rotor, fuselage, and tail rotor were investigated. For these simulations, a three-dimensional flow solver based on unstructured meshes was used, coupled with an overset mesh technique to handle relative motion among those components. To validate the flow solver, calculations were made for a UH-60A complete helicopter configuration at high-speed and low-speed forward flight conditions, and the unsteady airloads on the main rotor blade were compared to available flight test data and other calculated results. The results showed that the fuselage changed the rotor inflow distribution in the main rotor blade airloads. Such unsteady vibratory airloads were produced on the fuselage, which were nearly in-phase with the blade passage over the fuselage. The flow solver was then applied to the simulation of a generic complete helicopter configuration at various flight conditions, and the results were compared with those of the CAMRAD-II comprehensive analysis code. It was found that the main rotor blades strongly interact with a pair of disk-vortices at the outer edge of the rotor disk plane, which leads to high pulse airloads on the blade, and these airloads behave differently depending on the specific flight condition.

• 한국화재소방학회논문지
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• 제14권2호
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• pp.21-32
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• 2000

본 연구는 터널에서의 화재성상을 파악하기 위해 실물 실험의 대안으로서 축소 모형 실험을 수행하였고 또한 실험결과와 비고분석하기 위하여 터널내에서의 화재에 대하여 연기거동을 수치해석하였다. 터널내에서의 연기유동은 Buoyancy force에 의해 지배되므로 Froude scaling링에 의해 얻어진 축소법칙에 따라 실물터널을 1/20로 축소한 모형에서 실험 수행하였고 검증하였다. 여기서 얻어진 결과를 수치해석 결과와 비교하였다. 수치해석은 3D 비정 렬 격자, PISO 알고리즘, 부력 Plume 모델등을 사용하였다. 분석결과 실험과 수치해석 결과가 어느정도 일침함을 확인하였고, 연층의 전달 속도, 온도 구배, 하강 높이를 확인할 수 있었다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2004년도 춘계 학술대회논문집
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• pp.126-131
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• 2004

The interaction between the hypersonic free stream and the side jet flow at high altitudes is investigated by direct simulation Monte Carlo(DSMC) method. Since there is a great difference in density between the free stream and the side jet flow, the weighting factor technique which could control the number of simulation particles, is applied to calculate these two flows simultaneously. Chemical reactions are not considered in the calculation. For validation, the corner flow passing between a pair of plates that are perpendicularly attached is solved. The side jet flow is then injected into this comer flow and solution is found for the merged flow. Results are compared with the experiments. For a more realistic rocket model, the flow past a blunted cone cylinder shape is solved. The leeward or windward jet injection is merged with this flow. The effect on the rocket surface is observed at various flow angles. The lambda effect and the wake structure are found like low attitudes. High interaction between the free stream and the side jet flow is observed when the side jet is injected in the windward direction.

• 한국항공우주학회지
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• 제35권7호
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• pp.565-574
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• 2007

본 연구에서는 NACA 0012 익형 주위의 비교적 높은 레이놀즈수 유동장에 대한 Gurney 플랩과 제트 플랩을 혼용한 유동제어 기법의 유동제어 특성에 대하여 비정렬 격자계를 사용하는 수치적 기법을 이용하여 살펴보았다. 혼합제어 기법의 유동제어 특성을 파악하기 위하여 유동제어에 따른 공력계수 및 모멘트 계수의 변화를 혼합제어 기법을 구성하는 각각의 유동제어 기법들의 결과들과 비교하여 살펴보았다. 혼합제어 기법의 경우 제트 플랩만을 고려한 경우에 비하여 상당히 낮은 무차원 세기의 제트를 이용하여도 유사한 양력 향상 특성을 획득할 수 있었으며, Gurney 플랩만을 이용한 경우에 나타나는 항력의 증가를 완화시켜 주었다.

• 한국정보과학회논문지:시스템및이론
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• 제33권10호
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• pp.768-776
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• 2006

연결 정보가 없는 포인트 데이타가 주어졌을 때, 본 논문은 MLS(moving least-squares) 근사화 기법을 이용하여 포인트 데이타에 대해 근사화된 표면을 생성한다. 근사화된 표면에서의 각 포인트에 대해 지역적인 곡률과 곡률 미분 값을 측정 한 후, 딜러니 삼각화(Delaunay tessellation)를 통해 이웃간의 정보를 생성하게 되고, 연결된 포인트들 간의 제로-클로싱(zero-crossing)을 측정하여 특징 포인트들을 추출하고, 곡률 방향으로 추출 된 포인트들을 연결한다. 본 방법은 기존의 메쉬 데이타에서 특징 선을 찾는 방법과 비슷한 복잡도를 갖는다. 몇 개의 포인트-샘플 된 모델에 대해 특징 선 추출을 수행하며, 곡률의 크기에 따라 특징선의 두께를 조절하고 포인트-스플릿팅 방법에 의해 렌더링 한다.

• Nuclear Engineering and Technology
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• 제41권8호
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• pp.1045-1052
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• 2009

A calculation model is developed to predict the transient free surface flow on the containment floor following a loss-of-coolant accident (LOCA) of pressurized water reactors (PWR) for the use of debris transport evaluation. The model solves the two-dimensional Shallow Water Equation (SWE) using a finite volume method (FVM) with unstructured triangular meshes. The numerical scheme is based on a fully explicit predictor-corrector method to achieve a fast-running capability and numerical accuracy. The Harten-Lax-van Leer (HLL) scheme is used to reserve a shock-capturing capability in determining the convective flux term at the cell interface where the dry-to-wet changing proceeds. An experiment simulating a sudden break of a water reservoir with L-shape open channel is calculated for validation of the present model. It is shown that the present model agrees well with the experiment data, thus it can be justified for the free surface flow with accuracy. From the calculation of flow field over the simplified containment floor of APR1400, the important phenomena of free surface flow including propagations and interactions of waves generated by local water level distribution and reflection with a solid wall are found and the transient flow rates entering the Holdup Volume Tank (HVT) are obtained within a practical computational resource.

• 한국수자원학회:학술대회논문집
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• 한국수자원학회 2008년도 학술발표회 논문집
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• pp.1752-1756
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• 2008

A simple, accurate and efficient mesh generation technique, the cut-cell method, is able to represent an arbitrarily complex geometry. Both structured and unstructured grid meshes are used in this method. First, the numerical domain is constructed with regular Cartesian grids as a background grid and then the solid boundaries or bodies are cut out of the background Cartesian grids. As a result, some boundary cells can be contained two numerical conditions such as the flow and solid conditions, where the special treatment is needed to simulate such physical characteristics. The HLLC approximate Riemann solver, a Godunov-type finite volume method, is employed to discretize the advection terms in the governing equations. Also, the TVD-WAF method is applied on the Cartesian cut-cell grids to stabilize numerical results. Present method is validated for the rectangular dam break problems. Initially, a conventional grid is constructed with the Cartesian regular mesh only and then applied to the dam-break flow simulation. As a comparative simulation, a cut-cell grids are applied to represent the flow domain rotated with arbitrary angles. Numerical results from this study are compared with the results from the case of the Cartesian regular mesh only. A good agreement is achieved with other numerical results presented in the literature.

• Journal of Advanced Research in Ocean Engineering
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• 제4권2호
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• pp.78-85
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• 2018

This paper presents a study of the effects of the free surface to marine propeller including the mesh effect of the models. In the present study, we conduct the numerical simulation for propeller performance employing the openwater test. The numerical simulations compare the meshing strategies for the propeller and show the effects on both thrust and torque. OpenFOAM is applied to solve the propeller problem and then open water performances of KCS propeller (KP505) are estimated using a Reynold-averaged Navier-Stokes equations (RANS) solver and the turbulence of the $K-{\omega}$ SST model. Unstructured meshes are used in the numerical simulation employing hexahedral meshing for mesh generation. The arbitrary mesh interfacing (AMI) and multiple rotating frame (MRF) are compared to define the best meshing strategy. The meshing strategies are evaluated through 3 classifications, i.e., coarse, medium, and fine mesh. Thus, the propeller can be performed utilizing the best mesh strategy. The computational results are validated by comparison with the experimental results. The $K_T$, $K_Q$, and efficiency of the propeller are compared to an experimental result and for all of the meshing strategies. Thus, the simulations show the influence of meshing in order to perform the propeller performances.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2004년도 추계 학술대회논문집
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• pp.115-119
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• 2004

The effect of a continuous blowing or suction on an oscillating 2-D NACA0012 airfoil was investigated numerically for the dynamic stall control. The influence of control parameter variation was also studied in the view point of aerodynamic characteristics. The result showed that the blowing control kept a higher lift drag ratio before stall angle but the dynamic stall angle was not exceed to without control result. As the slot position was closer to leading edge, the positive control effect becomes greater. The stronger jet and the smaller jet angel made more favorable roles on the control performance. In the cases of the suction, the overall control features were similar to those of the blowing, but dynamic stall angle was increased, i.e. suction was more effective to control dynamic stall. It was also founded that the suction control was showed better control effect as the slot position moves to trail edge within thirty percentage of chord length. In the simulation for the jet strength and the jet angle control, the same tendencies were observed to those of blowing cases.