• Journal of Advanced Marine Engineering and Technology
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• 제23권2호
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• pp.216-225
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• 1999

Four turbulent $k-{varepsilon}$models(i.e standard model modified models with streamline curvature modification and/or preferential dissipation modification) are applied in order to analyze the tur-bulent flow of wall-attaching offset jet. The upwind numerical scheme was adopted in the present analyses. The streamline curvature modification results in slightly better prediction while the preferential dissipation modification does not. The obtained analytic results will be used as refer-ences for further study regarding Reynolds stress model. In addition this paper introduced a method of increasing nozzle outlet velocity gradually for numercal convergence. Even though the method was simple it was efficient in view of convergent speed CPU running time computer memory storage programming etc.

• 한국수자원학회논문집
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• 제30권3호
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• pp.201-210
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• 1997

$textsc{k}$-$\varepsilon$난류모델을 이용한 개수로 급축소부 흐름의 해석을 위한 수치모형을 개발하였고, 그 수치실험결과는 실험결과와 잘 일치하였다. 이는 난류모델에 의한 적절한 난류 와점성계수의 산정이라 생각된다. 유함수 및 유속분포의 분석을 통한 축소부 통과후 급변화 흐름의 수리특성을 분석하였고, 또한 난류 와점성계수의 분포를 분석하였다. 따라서 천수방정식의 점성항에 경험적인 유효점성계수의 도입보다는 흐름의 양상과 장소에 따라서 변화하는 난류와점성계수의 산정에 의한 급변화흐름의 해석이 필요하다.

• 대한토목학회논문집
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• 제10권4호
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• pp.151-158
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• 1990

불규칙파에 의하여 형성된 쇄파대에서의 확산은 여러가지 요인에 기인한다고 볼 수 있다. 개개파의 쇄파에너지로 발생되는 난류형상, 유속의 공간변화에 의한 영향, 쇄파대 폭의 확장과 함께 나타나는 잉여파응력(Excess Momentum Fluxes or Radiation Stresses)의 불규칙 중첩에 의한 영향 등이며 이로 인하여 연안류는 보다 완만한 곡선을 나타낼 것이다. 본 연구에서는 단순파를 중첩시켜 표현하는 스펙트럼파 모델을 ${\kappa}-{\varepsilon}$ 모델과 연안류 모델에 접속시켜 운용할 수 있는 모델시스템을 개발하여 현장 관측자료에 적용하였다. 적용결과, ${\kappa}-{\varepsilon}$ 모델은 쇄파대 확산에 있어 난류확산의 영향과 불규칙한 응력중첩이 영향 모두를 잘 재현할 수 있음을 알 수 있었다. 또한, 본 수치모형에서는 고려치 못하였지만, 파 스펙트럼간 에너지의 비선형 전도효과도 연안류분포에, 특히 수심이 작은 연안 가까이에서, 무시할 수 없을 정도의 영향을 미치는 것으로 나타났다.

• 한국전산유체공학회지
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• 제13권3호
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• pp.1-7
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• 2008

A supersonic base flow is computed to investigate the effect of the eddy viscosity coefficient to the linear ${\kappa}-{\varepsilon}$ turbulence models. Slight modifications to the eddy viscosity coefficient, which are based on the realizability condition, are given to the Launder-Sharma turbulence model so that present models satisfy the realizability condition. Numerical results for supersonic base flow show that turbulence models with the weaky-nonlinear eddy viscosity coefficient can lead to reasonable enhancements in the prediction of the velocity and turbulent kinetic energy profiles.

• 대한기계학회논문집B
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• 제23권1호
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• pp.82-91
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• 1999

A numerical analysis based on the three-dimensional Reynolds-averaged Navier-Stokes equation has been conducted to investigate the flow within a NASA rotor 67 transonic fan. General coordinate transformations are used to represent the complex blade geometry and an H-type grid is used. The governing equations are solved using implicit LU-SGS scheme for the time-marching integration and a standard ${\kappa}-{\varepsilon}$ model is used with wall functions for the turbulence modeling. The computations are compared with the experimental data and a detailed study of the flow structures near peak efficiency and near stall is presented. The calculated overall aerodynamic efficiency and three-dimensional shock system agree well with the laser anemometer data.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2000년도 춘계학술대회논문집B
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• pp.25-30
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• 2000

Plate and shell heat exchanger(P&SHE) has been applied to the refrigeration and air conditioning systems as evaporators or condensers fur their high efficiency and compactness. The purpose of this study is to analyze the characteristics of pressure drop in plate and shell heat exchanger. An experiment for single phase (low pressure drop in plate and shell heat exchanger was performed. Also numerical work was conducted using the FLUENT code for $ {\kappa}-{\varepsilon}$ model. The dependence of friction factor on geometrical Parameters was numerically investigated. The study examines the internal flow and the pressure distribution in the channel of plate and shell heat exchanger. The results of CFD analysis compared with experimental data, and the difference of frictor factor in plate side and shell side are 10% and 12%, respectively. Therefore, the CFD analysis model is effectively predict the performance of plate and shell heat exchanger.

• 대한기계학회논문집B
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• 제33권8호
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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.

• 대한기계학회논문집B
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• 제39권7호
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• pp.617-624
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• 2015

용존공기부상법이란 오염물에 미세기포를 부착하여 수표면으로 부상시킴으로써 이를 제거하는 수처리 방법이다. 본 연구에서는 난류모델에 따른 용존공기부상조 내부 유동해석의 변화를 고찰하기 위해 물과 기포의 혼합물에 대한 2상 유동을 모사하였다. 이때, 주어진 용존공기부상조 형상 및 조건에 대하여 다양한 난류모델에 따른 용존공기부상법 내부의 미세기포 분포량, 계산시간 및 수렴성 등을 비교하였으며, 그 결과 기존에 주로 사용되었던 표준 ${\kappa}-{\varepsilon}$ 모델이 타 난류모델과는 다른 거동을 예측하는 것으로 확인되었다.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2000년도 춘계학술대회논문집B
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• pp.479-484
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• 2000

A Navier-stokes based finite volume method has been developed to analyze an incompressible, steady state, turbulent wall-jet flow. The standard k-e model, the RNG ${\kappa}-{\varepsilon}$ model and their nonlinear counterparts are adopted as a closure relationship. Comparison with the experimental data shows that a linear ${\kappa}-{\varepsilon}$ model performs satisfatorily for two-dimensional wall-jet flows. However, as the flow becomes three dimensional, the linear model fails to predict the spanwise jet growth accurately and the nonlinear model needs to be adopted to capture three-dimensional flow characteristics.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2008년 추계학술대회논문집
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• pp.297-301
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• 2008

The flight vehicles have cavities such as wheel wells and bomb bays. The flow around a cavity is characterized as unsteady flow because of the formation and dissipation of vortices due to the interaction between the freestream shear layer and cavity internal flow, the generation of shock and expansion waves. Resonance phenomena can damage the structures around the cavity and negatively affect aerodynamic performance and stability. The flow field is observed to oscillate in the "shear layer mode" with low aspect ratio. In the present study, numerical analysis was performed for cavity flows by the unsteady compressible three dimensional Reynolds-Averaged Navier-Stokes (RANS) equations with Wilcox's ${\kappa}-{\varepsilon}$ turbulence model. The flow field is observed to oscillate in the "shear layer mode" with large aspect ratio. Based on the SPL(Sound Pressure Level) analysis of the pressure variation at the cavity trailing edge, the dominant frequency was analyzed and compared with the results of Rossiter's formul. The aero-acoustic wave analyzed with CPD(Correlation of Pressure Distribution).