• 한국수자원학회논문집
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• 제48권12호
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• pp.1023-1035
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• 2015

본 연구에서는 해수-담수-해안대수층의 비선형 상호작용을 직접 해석할 있는 PBM(Porous Body Model) 기반의 3차원 N-S Solver인 LES-WASS-3D ver 2.0을 적용하며, 해안대수층의 해수침투모의를 수행하였다. 이와 같은 N-S Solver를 적용한 해안대수층의 해수침투모의는 국내 최초 수행되는 것일 뿐만 아니라, 국외적으로도 찾아보기 어려운 새로운 수치해석방법이라고 할 수 있다. 먼저 적용하는 수치모델을 검증하기 위하여 해안대수층의 해수-담수 경계면에 관한 수리모형실험결과와 비교 검토하여 수치모델의 타당성 및 유효성을 확인하였다. 그리고 해수위 및 지하수위 변화를 고려한 해안대수층 내의 해수침투모의를 수행하여 해수위-지하수위 차와 해수위의 비(${\Delta}h/h$)의 증가에 따른 해안대수층 내의 유동장 그리고 해수-담수 경계면 분포 특성에 관하여 논의하였다. 또한 기존의 비확산 수치모델에서 도출할 수 없었던, ${\Delta}h/h$에 따른 해안대수층 내의 연직 염분농도로 부터 해수침투 특성을 파악하였으며, 최종적으로 지표화 할 수 있는 ${\Delta}h/h$가 해안대수층 내의 해수침투거리에 미치는 영향에 대하여 분석하였다. 이 결과로부터 ${\Delta}h/h$가 작을수록 해안대수층 내의 해수침투가 약해지는 메커니즘을 이해할 수 있었다.

• 전자공학회논문지D
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• 제34D권8호
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• pp.15-25
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• 1997

The integration method of carier concentrations to redcue the discretization error of th box integratio method used in the discretization of the three-dimensional poisson's equation is presented. The carrier concentration is approximated in the closed form as an exponential function of the linearly varying potential in the element. The presented method is implemented in the three-dimensional poisson's equation solver running under the windows 95. The accuracy and the convergence chaacteristics of the three-dimensional poisson's equation solver are compared with those of DAVINCI for the PN junction diode and the n-MOSFET under the thermal equilibrium and the DC reverse bias. The potential distributions of the simulatied devices from the three-dimensional poisson's equation solver, compared with those of DAVINCI, has a relative error within 2.8%. The average number of iterations needed to obtain the solution of the PN junction diode and the n-MOSFET using the presented method are 11.47 and 11.16 while the those of DAVINCI are 21.73 and 23.0 respectively.

• 한국전산구조공학회논문집
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• 제23권6호
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• pp.675-682
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• 2010

The flood impact pressure acting on a vertical wall resulting from a dam-breaking problem is simulated using a navier-Stokes(N-S) solver. The N-S solver uses Eulerian Finite Volume Method(FVM) along with Volume Of Fluid(VOF) method for 2-D incompressible free surface flows. A Split Lagrangian Advection(SLA) scheme for VOF method is implemented in this paper. The SLA scheme is developed based on an algorithm of Piecewise Linear Interface Calculation(PLIC). The coupling between the continuity and momentum equations is affected by using a well-known Semi-Implicit Method for Pressure-Linked Equations (SIMPLE) algorithm. Several two-dimensional numerical simulations of the dam-breaking problem are presented to validate the accuracy and demonstrate the capability of the present algorithm. The significance of the time step and grid resolution are also discussed. The computational results are compared with experimental data and with computations by other numerical methods. The results showed a favorable agreement of water impact pressure as well as the global fluid motion.

• 한국전산유체공학회지
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• 제5권2호
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• pp.20-27
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• 2000

An unstructured implicit Euler solver is parallelized on a Cray T3E. Spatial discretization is accomplished by a cell-centered finite volume formulation using an upwind flux differencing. Time is advanced by the Gauss-Seidel implicit scheme. Domain decomposition is accomplished by using the k-way n-partitioning method developed by Karypis. In order to analyze the parallel performance of the solver, flows over a 2-D NACA 0012 airfoil and 3-D F-5 wing were investigated.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 1999년도 추계 학술대회논문집
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• pp.193-200
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• 1999

An unstructured implicit Euler solver is parallelized on a Cray T3E. Spatial discretization is accomplished by a cell-centered finite volume formulation using an unpwind flux differencing. Time is advanced by the Gauss-Seidel implicit scheme. Domain decomposition is accomplished by using the k-way N-partitioning method developed by Karypis. In order to analyze the parallel performance of the solver, flows over a 2-D NACA 0012 airfoil and a 3-D F-5 wing were investigated.

• 한국항공우주학회지
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• 제37권10호
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• pp.947-954
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• 2009

본 연구에서는 다화학종 희박유동의 해석을 위해, GH(Generalized Hydrodynamic) 방정식을 기반으로 한 축대칭 유동 해석이 가능한 다화학종 GH 수치해석 기법을 전산유체역학 수치해석자로서 개발하였다. 최초로 구현된 다화학종 GH 수치기법은 축대칭 형상의 물체 주위의 극초음속 희박유동을 대상으로 하여, DSMC(Direct Simulation Monte Carlo) 및 N-S(Navier-Stokes) 방정식의 결과와의 비교를 통해 정확도를 검증하고자 하였다. GH 해석자의 정확도 향상을 위해 고체 벽면에서의 여러 가지 slip-wall 경계조건을 적용하고 각각의 결과를 비교하였다. 또한, 높은 Knudsen 수의 1차원 수직 충격파 구조 문제를 통해 GH 방정식의 엔트로피 특성 및 정확성을 고찰하였다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 1995년도 추계 학술대회논문집
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• pp.49-54
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• 1995

A numerical analysis on the effect of the front shape on the aerodynamic characteristics of HST model is made, using FVM based general purpose 3D Navier-Stokes eq. solver, TURBO-3D program. Numerical solutions are compared with each case of different front shape for HST model. The result shows a good quantitative aerodynamic characteristic tendencies for variation of front shape of HST. Thus it may be used as a basis in the design of the shape of real HST.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2011년 춘계학술대회논문집
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• pp.343-349
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• 2011

A loosely coupling method is adopted to combine a computational fluid dynamics (CFD) solver and the comprehensive structural dynamics (CSD) code, CAMRAD II, in a systematic manner to correlate the airloads, vortex trajectories, blade motions, and structural loads of the HART I rotor in descending flight condition. A three-dimensional compressible Navier-Stokes solver, KFLOW, using chimera overlapped grids has been used to simulate unsteady flow phenomena over helicopter rotor blades. The number of grids used in the CFD computation is about 24 million for the isolated rotor and about 37.6 million for the rotor-fuselage configuration while keeping the background grid spacing identical as 10% blade chord length. The prediction of blade airloads is compared with the experimental data. The current method predicts reasonably well the BVI phenomena of blade airloads. The vortices generated from the fuselage have an influence on airloads in the 1st and 4th quadrants of rotor disk. It appeared that presence of the pylon cylinder resulted in complex turbulent flow field behind the hub center.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2005년도 추계 학술대회논문집
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• pp.145-150
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• 2005

Generally, Compressible Navier-Stokes codes are used to solve high mach number flows. But, Most of high mach number flows embrace low mach number flows. This phenomenon results in low convergence rate and non-physical solution in CFD analysis. So Many researchers developed preconditioning technique to solve these problems. This Study presents how to modify previous compressible N-S computer code with little changes of structure into preconditioned compressible N-S code applying Roe's Approximate Riemann Solver. And this study show developed preconditioning code is very well operated at all mach number flows.

• Nuclear Engineering and Technology
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• 제49권6호
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• pp.1114-1124
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• 2017

Acceleration/preconditioning strategies available in the SCEPTRE radiation transport code are described. A flexible transport synthetic acceleration (TSA) algorithm that uses a low-order discrete-ordinates ($S_N$) or spherical-harmonics ($P_N$) solve to accelerate convergence of a high-order $S_N$ source-iteration (SI) solve is described. Convergence of the low-order solves can be further accelerated by applying off-the-shelf incomplete-factorization or algebraic-multigrid methods. Also available is an algorithm that uses a generalized minimum residual (GMRES) iterative method rather than SI for convergence, using a parallel sweep-based solver to build up a Krylov subspace. TSA has been applied as a preconditioner to accelerate the convergence of the GMRES iterations. The methods are applied to several problems involving electron transport and problems with artificial cross sections with large scattering ratios. These methods were compared and evaluated by considering material discontinuities and scattering anisotropy. Observed accelerations obtained are highly problem dependent, but speedup factors around 10 have been observed in typical applications.