• 한국전산유체공학회:학술대회논문집
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• 1995.10a
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• pp.132-137
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• 1995

Numerical analysis is conducted on the deformation of free surface of magnetic fluid. Steady magnetic fields are induced by a circular current loop. Governing equations of magnetic fields are solved by using the concept of vector potential. The free surface of magnetic fluid is formed by the balance of surface force, gravity, pressure difference, magnetic normal pressure and magnetic body force. The deformations of free surface of magnetic fluid are qualitatively clarified. And, the patterns of steady non-uniform magnetic fields induced by a circular current loop are quantitatively presented.

• Journal of Scientific & Technological Knowledge Infrastructure
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• s.6
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• pp.136-139
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• 2001

풍동과 같은 고가의 실험 장비가 필요하고 결과를 얻는데까지 많은 시간과 비용이 소요되는 단점이 있습니다. 전산유체역학은 이러한 문제점들을 보완할 수 있는 휼륭한 대안으로 인정받고 있습니다. 자연계에서 공기나 물 등의 유체가 우리의 관심 대상인 비행기, 자동차 등의 물체 주위를 흘러갈 때 생기는 물리 현상들은 보존의 법칙과 열역할 법칙에서 얻어지는 편미분 방정식들로 나타낼 수 있습니다. 이러한 자연계의 법칙을 나타내는 복잡한 방정식을 컴퓨터로 해석하여 데이터를 얻는 수치적인 실험 혹은 시물레이션을 전산유체역할 이라고 부릅니다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.12
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• pp.1139-1145
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• 2008

numerical study on the coupled fluid-structure for a rotor blade in hover was conducted. Computational fluid dynamics code with enhanced wake-capturing capability is coupled with a simple structural dynamics code based on Euler-Bernoulli's beam equation. The numerical results show a reasonable blade structural deformation and aerodynamic characteristics.

• Cement Symposium
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• no.29
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• pp.168-178
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• 2002

• 한국전산유체공학회:학술대회논문집
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• 1999.05a
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• pp.131-136
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• 1999

박리를 수반하는 진동하는 이차원 익형 주위의 비정상 유동장에 대해 SST 난류 모델을 이용하여 해석을 수행하였다. SST 모델은 정상 유동장 해석에서 기존의 난류 모델에 비해 우수한 성능을 보인다고 알려져 있으나 큰 박리영역에서 공력 계수의 진동 현상을 보이는 등 비정상 유동장 해석에 문제점을 보이고 있다. 본 논문에서는 이러한 공력 계수의 진동 현상이 SST 모델을 이차원으로 확장하는 과정에서 발생한 것임을 밝히고 이에 대한 보완을 통하여 수정된 SST 모델을 제시하고자 한다. SST 모델의 기본이 되었던 BSL 모델 및 SST 모델, 수정된 SST 모델을 사용하여 정상 유동장과 비정상 유동장 해석을 수행하여 각 모델의 난류 유동장 해석 특성을 비교하고 이를 통하여 수정된 SST 모델이 박리를 수반하는 비정상 유동장 해석에서 원래의 SST 모델에 비해 향상된 결과를 나타남을 알 수 있었다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2001.04a
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• pp.73-75
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• 2001

• 한국전산유체공학회:학술대회논문집
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• 2010.05a
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• pp.78-82
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• 2010

An integrated multi-disciplinary design system plays a critical role in the preliminary design of an aircraft. In this paper such system is developed for the multi-disciplinary computation and design; aerodynamics elasticity, and radio frequency stealth. Common data base of geometry and structured grids is generated and used for aerodynamic, structural and eletromagnetics analysis. The Navier-Stokes CFD, FEM, and CEM technique are used for aerodynamic, structural, and RF stealth computations respectively.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.5
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• pp.37-43
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• 2003

Parallel computing method is widely used in the computational fluid dynamics for efficient numerical analysis. Nowadays, low cost Linux cluster computers substitute for traditional supercomputers with parallel computing shcemes. The performance of nemerical solvers on an Linux cluster computer is highly dependent not on the performance of processors but on the performance of network devices in the cluster system. In this paper, we investigated the effects of the network devices such as Myrinet2000, gigabit ethernet, and fast ethernet on the performance of the cluster system by using some benchmark programs such as Netpipe, LINPACK, NAS NPB, and MPINS2D Navier-Stokes solvers. Finally, upon this investigation, we will suggest the method for building high performance low cost Linux cluster system in the computational fluid dynamics analysis.

• 한국전산유체공학회:학술대회논문집
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• 2007.10a
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• pp.167-170
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• 2007

In the present paper, wall correction method is reviewed and applied to the numerical experimental results obtained at the wind tunnel condition. The corrected lift coefficient agrees well with the reference data generated from the grid having very far boundary. However the corrected drag coefficient presents some deviation from the reference data.

• 한국전산유체공학회:학술대회논문집
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• 2010.05a
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• pp.71-77
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• 2010

As a hybrid model of continuum motion description which combines the advantages of classical kinematical descriptions i.e. Lagrangian and Eulerian description, the ALE (Arbitrary Lagrangian Eulerian) description is adopted for the simulation of a fluid-structure interaction of solid propellant rocket interior. The fluid-structure interaction phenomenon with the deformation of solid domain during the simulation. The developed solver is applied flow and propellant structure. The computed results show complex flow physics in the combustion chamber and the behavior of a solid propellant deformation.