• Transactions of the Korean Society of Mechanical Engineers B
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• v.33 no.8
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• pp.635-642
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• 2009

The three-dimensional turbulent wingtip vortex flows have been examined in the present study by using the commercial code FLUENT. The standard ${\kappa}-{\varepsilon}$ model is used as a closure relationship. The wing is constructed by using an elliptic body whose aspect ratio is 3.8 and the NACA 16-020 airfoil section. The simulations for various angle attack (${\alpha}=0^{\circ}$, $5^{\circ}$, and $10^{\circ}$) are carried out. The effect of Reynolds number is also investigated in this study. As the angle attack increases, the wingtip vortex becomes stronger. However, the relative vortex strength to inlet velocity decreases as Reynolds number increases.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.6 no.4
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• pp.302-308
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• 2005

The temperature distribution and fluid flow in the chamber was investigated using FLUENT code. It provides comprehensive modeling capabilities for a wide range of incompressible or compressible and laminar or turbulent fluid flow problems. And a broad range of mathematical models for transport phenomena is combined with the ability to model for complex geometries. The geometry of the chamber was very complex, and a simplified model of the chamber was used in the simulation experiment. It was important that the temperature deviation of test site. This datum were provided in the improving the control algorithm. Using this algorithm, the results were with in $0.1^{\circ}C.$

• Fire Science and Engineering
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• v.28 no.4
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• pp.35-43
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• 2014

The prediction performance of 9 model sets, which combine 3 turbulent models and 3 combustion models, was investigated numerically for turbulent partially-premixed jet flame. The standard ${\kappa}-{\varepsilon}$ (SKE), Realizable ${\kappa}-{\varepsilon}$ (RKE) and Reynolds stress model (RSM) were used as a turbulence model, and the eddy dissipation concept (EDC), steady laminar flamelet (SLF) and unsteady laminar flamelet model (ULF) were also adopted as a combustion model. The prediction performance of those 9 model sets was evaluated quantitatively and qualitatively for Sandia D flame of which flame structure was measured precisely. The flame length was predicted as, from longest to shortest, RSM > SKE > RKE, and the RKE predicted the flame length of the jet flame much shorter than experiment. The flame temperature was over predicted by the combination of RSM + SLF or RSM + ULF while the flame length obtained by RSM + SLF and RSM + ULF was well agreed with the experiment. The combination of SKE + SLF and SKE + ULF predicts well the flame length as well as the temperature distribution. The SKE turbulence model was most superior to the other turbulent models, and SKE + ULF showed the best prediction performance for the structure of turbulent partially-premixed jet flame.

• Journal of the Korean Society of Propulsion Engineers
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• v.7 no.2
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• pp.7-14
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• 2003

Computational work using the axisymmetric, compressible, Navier-Stokes Equations is carried out to predict the discharge coefficient of mass flow through a micro-critical nozzle. Several kinds of turbulence models and wall functions are employed to validate the computational predictions. The computed results are compared with the previous experimented ones. The present computations predict the experimental discharge coefficients with a reasonable accuracy. It is found that the standard $\kappa$-$\varepsilon$turbulence model with the standard wall function gives a best prediction of the discharge coefficients. The displacement thickness of the nozzle wall boundary layer is evaluated at the nozzle throat and is well compared to a prediction obtained by an empirical equation. The resulting displacement thickness of the wall boundary layer is about 2% to 0.6% of the diameter of the nozzle throat for the Reynolds numbers of 2000 to 20000.

• Proceedings of the KSME Conference
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• 2000.04b
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• pp.568-573
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• 2000

In this study, experimental and numerical analyses are carried out to investigate the performance of centrifugal pump with various air admitting conditions. Experiments on pump performance under air-water two-phase flow n accomplished using a centrifugal pump with semi-open type impeller having three, five and seven blades, respectively. Also, the numerical analysis of turbulent air-water two-phase flow using finite volume method has been carried out to obtain the pressure, velocities and void fraction on the basis of a so-called bubbly flow model with the constant size and shape of cavity. The results obtained through this study show the reasonable agreements within the range of bubbly flow regime. There are promising developments concerning application of the present study for the flow in a centrifugal pump with two-phase flow conditions and efforts must be followed to improve the turbulence model and two-phase flow model for turbomachinery.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.39 no.7
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• pp.617-624
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• 2015

The dissolved air flotation (DAF) system is a water treatment process that removes contaminants by attaching micro bubbles to them, causing them to float to the water surface. In the present study, two-phase flow of air-water mixture is simulated to investigate changes in the internal flow analysis of DAF systems caused by using different turbulence models. Internal micro bubble distribution, velocity, and computation time are compared between several turbulence models for a given DAF geometry and condition. As a result, it is observed that the standard ${\kappa}-{\varepsilon}$ model, which has been frequently used in previous research, predicts somewhat different behavior than other turbulence models.

• Fire Science and Engineering
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• v.19 no.1 s.57
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• pp.87-92
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• 2005

In this paper, numerical simulation are conducted to predict the characteristics of the heat transfer and smoke flow and evacuation in the road tunnel. Fire source are used about 30 MW and the turbulent flow characteristics are considered by standard k-epsilon turbulent model. The effect of transient thermal behavior and disaster prevention can be used for designing the road tunnel.

• Proceedings of the Korea Water Resources Association Conference
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• 2019.05a
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• pp.90-90
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• 2019

본 연구에서는 SWASH(Simulating WAves till SHore) 모형의 염분분포 해석의 정확성을 평가하기 위해 Goswami et al.(2007)의 모형실험을 재현하였다. SWASH모형은 Delft 대학에서 개발된 비정수압수치모형으로 연직방향으로 층(layer)을 나누어 자유수면변위를 정확하게 예측하고 표준 ${\kappa}-{\varepsilon}$ 난류모델을 이용해 염분, 온도 및 침전물 등의 난류확산을 계산한다. 우선 Goswami et al.(2007)의 모형실험 중 정상상태의 모형실험을 이용해 층수에 따른 수치모형의 정확도를 평가하였다. SWASH 모형의 층수를 늘리며 수치모의를 수행한 결과, 층수가 늘어날수록 종, 횡 방향의 염분농도 분포가 정확하게 나타나는 것을 확인하였다. 추가로 SWASH 수치모형을 이용해 염수침투 및 후퇴 상태의 모형실험도 수치모의하였다. 염수의 공급에 따라 시간에 따른 염분농도 분포가 변화하는 것을 확인하였다. 또한 연직방향의 층수가 많은 경우 모형실험의 결과와 비교적 잘 일치하는 것을 확인할 수 있다. 따라서 연직방향의 층수를 늘려감에 따라 수심방향으로 더 정밀한 염분분포 해석이 가능하다는 것을 알 수 있다. 그러나 연직방향으로 많은 층을 나눈 경우 계산시간이 증가하기 때문에 수심이 작거나 연직방향의 염분농도 분포가 중요하지 않은 경우라면 적절한 층수(5~10 layer)를 고려해 수치모의를 수행하는 것이 시간과 비용측면에서 더욱 경제적이라고 할 수 있다.

• Journal of the Korean Society of Propulsion Engineers
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• v.3 no.4
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• pp.58-66
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• 1999

The flow characteristics of supersonic ejectors is often subject to compressibility, unsteadiness and shock wave systems. The numerical works carried out thus far have been of one-dimensional analyses or some Computational Fluid Dynamics(CFD) which has been applied to only a very simplified configuration. For the design of effective ejector-pump systems the effects of secondary mass flow on the supersonic ejector flow should be fully understood. In the present work the supersonic ejector-pump flows with a secondary mass flow were simulated using CFD. A fully implicit finite volume scheme was applied to axisymmetric compressible Navier-Stokes equations. The standard two-equation turbulence model was employed to predict turbulent stresses. The results obtained showed that the flow characteristics of constant area mixing tube types were nearly independent of the secondary flow rate, but the flow fields of ejector system with the second-throat were strongly dependent on the secondary flow rate due to the effect of the back pressure near the primary nozzle exit.