• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 1996년도 춘계 학술대회논문집
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• pp.46-51
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• 1996

The flow field around a three dimensional minivan-like body has been simulated. This study solves 3-D unsteady incompressible Navier-Stokes equations on a non-orthogonal curvilinear coordinate system using second-order accurate schemes for the time derivatives, and third/second-order scheme for the spatial derivatives. The Marker-and-Cell concept is applied to efficiently solve continuity equation. The fourth -order artificial damping is added to the continuity equation for numerical stability. A H-H type multi-block grid system is generated around a three dimensional minivan-like body. Turbulent flows have been modeled by the Baldwin-Lomax turbulent model. The simulation shows three dimensional vortex-pair just behind body. And the flow separation is also observed the rear of the body. It has concluded that the results of present study properly agree with physical flow phenomena.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 1998년도 춘계 학술대회논문집
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• pp.99-109
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• 1998

This paper describes the analysis of flow and aeroacoustic field around a car-like body. The governing equations, 3-D unsteady incompressible Navier-Stokes equations, are solved with the iterative time marching scheme. The Chimera grid technique has been applied to efficiently simulate the flow around the side-view mirror, After the flow field analysis has been converged, the aerodynamic noise analysis of the side-view mirror has been performed by solving Ffowcs Williams and Hawkings equation. From the present numerical simulation, the A- and C-pillar vortex are evidently shown and the aerodynamic noise level induced by the side-view mirror is predicted to about 100dB.

• International Journal of Aeronautical and Space Sciences
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• 제11권1호
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• pp.41-48
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• 2010

In the present study, the turbulent flow fields around a circular cylinder at $Re=3.6{\times}10^6$ were investigated based on an unstructured mesh technique, and the comparisons between URANS(S-A, SST) and hybrid RANS/LES(DES, SAS) methods for the simulation of high Reynolds number flow have been conducted. For this purpose, unsteady characteristics of vortex shedding and time-averaged quantities were compared. A quasi-steady solution-adaptive mesh refinement was also made for the URANS and hybrid RANS/LES approaches. The results showed that the simple changes in the turbulent length scale or source term of turbulent models made the flow fields less dissipative and more realistic in hybrid RANS/LES methods than the URANS approaches.

• 한국전산유체공학회지
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• 제12권4호
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• pp.61-67
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• 2007

Numerical simulation of laminar flow over two spheres in a side-by-side arrangement is carried out to investigate the effect of the inter-sphere spacing on the flow characteristics. The Reynolds numbers considered are 100, 250, and 300, covering the steady axisymmetric, steady planar-symmetric, and unsteady planar-symmetric flows in the case of a single sphere. Results show that the drag and lift coefficients and wake structures are significantly modified depending on both the Reynolds number and the spacing between the spheres. At Re=100, the flow is steady planar-symmetric irrespective of the spacing, but it shows some variation according to the spacing at Re=250 and 300. That is, the flow maintains planar symmetry of the single-sphere wake at large spacings, while it loses the symmetry at small spacings due to the generation of new asymmetric vortical structures. It is also shown that the drag and lift coefficients generally increase with decreasing inter-sphere spacing because the high pressure region is formed near the gap between the spheres.

• 대한전기학회논문지:전기기기및에너지변환시스템부문B
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• 제49권4호
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• pp.233-239
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• 2000

There are many difficult problems in analyzing the gas flow in puffer type circuit breaker such as complex geometry, moving boundary, shock wave and so on. To predict the interruption performance accurately, these should be considered in the simulation. In this paper, the analysis procedure of the cold gas flow in the circuit breaker is presented. Euler equation is solved by FVFLIC method which is an explicit time difference scheme for an unsteady flow computation. Moving boundaries are treated with a cell elimination-addition technique. The pressure and density in front of piston are calculated from the rate of the cell volume change. The presented method is applied to the real circuit breaker model and the pressure in front of the piston is good agreement with the experimental one.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2012년도 제38회 춘계학술대회논문집
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• pp.309-317
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• 2012

Recent years have witnessed the use of micro shock tube in various engineering applications like micro combustion, micro propulsion, particle delivery systems etc. The flow characteristics occurring in the micro shock tube shows a considerable deviation from that of well established conventional macro shock tube due to very low Reynolds number and high Knudsen number effects. Also the diaphragm rupture process, which is considered to be instantaneous process in many of the conventional shock tubes, will be crucial for micro shock tubes in determining the near diaphragm flow field and shock formation. In the present study, an axi-symmetric CFD method has been applied to simulate the micro shock tube, with Maxwell's slip velocity and temperature jump boundary conditions. The effects of finite diaphragm rupture process on the flow field and the shock formation was investigated, in detail. The results show that the shock strength attenuates rapidly as it propagates through micro shock tubes.

• 한국수자원학회논문집
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• 제49권1호
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• pp.29-39
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• 2016

강변저류지를 홍수방어대책에 포함시키기 위해서는 정확한 홍수조절효과 산정이 필요하며, 이를 위해 현재 실무에서는 1차원 부정류 수치모형인 HEC-RAS를 사용하고 있다. 그러나 강변저류지의 저류용량이 부족한 경우에 발생하는 잠긴 횡월류 흐름에 대해서는 HEC-RAS 부정류 수치모의의 정확도 분석이 수행되지 않았다. 따라서 본 연구에서는 직선수로에 강변저류지를 설치한 경우에 대하여 횡월류부의 다양한 흐름 형태를 재현할 수 있는 부정류 수리실험을 수행하였다. 또한 부정류 수리실험 결과를 이용하여 HEC-RAS 모형의 부정류 수치모의 결과의 정확도를 분석하여 하도 내 수위 오차 및 강변저류지의 홍수조절효과 산정 오차를 제시하였다. 분석 결과 횡월류부에서 잠긴 횡월류 흐름이 발생하는 경우에 대한 HEC-RAS의 수위 계산 결과는 최대 -5% 오차를 보였으며, 홍수조절효과 오차는 최대 2.4%로 나타나 HEC-RAS의 부정류 모의 결과가 비교적 정확한 것을 확인하였다.

• 한국전산유체공학회지
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• 제4권1호
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• pp.19-26
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• 1999

This paper describes a numerical method for predicting the incompressible unsteady laminar three-dimensional flows with free-surface. The Navier-Stokes equations governing the flows have been discretized by means of finite-difference approximations, and the resulting equations have been solved via the SIMPLE-C algorithm. The free-surface is defined by the motion of a set of marker particles and the interface behaviour was investigated by means of a "Lagrangian" technique. Using the GALA concept of Spalding, the conventional mass continuity equation is modified to form a volumetric or bulk-continuity equation. The use of this bulk-continuity relation allows the hydrodynamic variables to be computed over the entire flow domain including both liquid and gas regions. Thus, the free-surface boundary conditions are imposed implicitly and the problem formulation is greatly simplified. The numerical procedure is validated by comparing the predicted results of a periodic standing waves problems with analytic solutions. The results show that this numerical method produces accurate and physically realistic predictions of three-dimensional free-surface flows.

• 물과 미래
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• 제15권1호
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• pp.57-62
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• 1982

본 연구에서는 1차원 부정류를 나타내는 Saint Venant의 편미분방정식을 Preissmann의 Implicit 기법에 의하여 유한차분방정식을 구성한 후에 Double sweep 알고리죽을 적용하여 해석하는 문제를 다루었으며, 본 차분방정식의 안정성과 정도를 검토하였고 $C_r$, $\theta$ 및 Chezy 계수 등의 영향을 1차원 Seiche 운동에 관한 수치실험을 통하여 분석하여 보았는 바, 그 내용은 다음과 같다. 1. 보조관계식을 활용함으로써 Double sweep 알고리즘의 적용이 가능하였다. 2. 해석결과에 가장 큰 영향을 미치는 인자는 $C_r$, $\theta$ 및 Chezy 계수인 바, 높은 정도의 결과를 얻기 위해서 $C_r$은 1보다 너무 큰 값은 피해야 될 것이며, $\theta$의 적합한 범위는 0.6<$\theta$<1.0이였다. 3. 본 모형은 1차원 장파의 전파에 적용하였던 바 안정된 결과를 보였다.

• 한국항공우주학회지
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• 제35권6호
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• pp.474-482
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• 2007

초음속 공중발사 로켓의 모선분리에 대한 유동해석을 수행하였다. 전기체 형상의 모선(F-4E Phantom)에서 분리되는 로켓주변 유동장의 정상/비정상 유동해석을 위해 압축성 Navier-Stokes 방정식이 사용되었으며, 해석결과는 모선과 로켓간의 충격파-팽창파 간섭효과를 잘 보여주고 있다. 무게중심의 변화에 따른 로켓의 거동을 예측하기 위하여 세 가지 경우에 대한 전산해석을 수행하였으며, 결과적으로 초음속 공중발사 로켓의 안전한 모선분리를 위한 설계 가이드라인을 제시하였다.