• 해양환경안전학회:학술대회논문집
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• 해양환경안전학회 2005년도 추계학술대회지
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• pp.153-158
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• 2005

표면에 부착된 수직벽 후방의 난류전단흐름을 입자영상유속계를 이용하여 조사하였다. 하부 틈새를 갖는 수직벽 후류영역에서는 박리 후 비정상적인(unsteady) 재순환 영역이 형성되었으며, 약 x=3H위치에서 전단층의 재부착 및 난류경계층으로의 재발달 과정이 나타났다. 수직벽 직전의 오목한(concave) 유선곡률과 수직벽 후방의 볼록한(convex)유선곡률의 영향은 수직벽 주위에서 가장 크게 나타나고, 하류로 나아감에 따라 전단층 주위 유체의 유입 등으로 그 영향이 박리 전단층 내에서 커다란 와구조가 연속적으로 발생하였다.

• 대한기계학회논문집B
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• 제39권10호
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• pp.795-803
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• 2015

본 연구에서는 발전용 터빈 제 1 단 동익 흡입면에서 발달하는 경계층유동에 대하여 체계적으로 연구하였다. 이를 위해 흡입면에서 열부하가 급격하게 변화하는 대표적인 영역에 대하여, 경계층의 평균 유속, 난류강도, 에너지스펙트럼 등을 측정하였다. 그 결과 흡입면 경계층유동이 층류에서 난류 경계층으로 천이됨을 확인할 수 있었고, 이 천이경로는 박리버블의 전단층에서 주로 발생하는 박리유동 천이로 확인되었다. 흡입면에서 열부하의 최소값이 존재하는 곳은 흡입면 경계층유동의 천이가 시작되는 위치에 해당하며, 열부하가 최대인 곳은 박리유동 천이가 모두 마무리되어 벽근처에 강력한 난류유동이 존재하는 곳과 일치하였다. 에너지스펙트럼의 측정을 통하여, 흡입면 경계층의 박리유동 천이 전후에 나타나는 난류운동에너지의 주파수 특성을 자세히 파악할 수 있었다.

• 대한기계학회논문집
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• 제13권1호
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• pp.178-189
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• 1989

본 연구에서는 우선 승용차의 1/10 모형의 형상을 더욱 단순화시킨 2차원 자동차형 물체를 대상으로 하여 그 주위의 압력, 속도 및 난류량의 분포를 측정하고, 또한 울터프트(wool tuft)를 이용한 유동가시화법으로 후류구조를 파악함으로써 향후 계속될 실험적 및 수치해석적 연구의 기초를 마련하고자 한다.

• 한국정밀공학회지
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• 제30권5호
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• pp.544-551
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• 2013

Recently high speed mixer, which is mixing, grinding, dispersion for liquid-liquid material, has been widely used several industries such as food, cosmetics, pharmaceuticals, fine chemicals, electronic material. This high speed mixer has a core element part called particle separation device. Particle separation device, which makes mixed liquid and liquid material using shear forces from a rotor and a stator, is a decisive factor in the distributed parts. In this study, we examined the velocity distribution of the two models of particle separation device using computation fluid dynamics, so that we were able to see the difference of the velocity distribution according to the shape. Also, by experiment, we observed that the use of rotor-screen type is deemed more suitable in case of accurately considering the effect of improving of the dispersibility through the circulation of the future.

• 산업기술연구
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• 제17권
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• pp.183-189
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• 1997

The computation of the flow around a supercritical airfoil with a divergent trailing edge(DTE) modification(DLBA 243) is compared to that of original supercritical airfoil(DLBA 186). For this computation, Reynolds-Averaged Navier-Stokes equations are solved with a linearized block implicit ADI method and a mixing length turbulence model. Results show the effects of the shock and separated flow regions on drag reduction due to DTE modification. Results also show that DTE modification accelerates the boundary layer flow near the trailing edges which has an effect similar to a chordwise extension that increases circulation and is consistent with the calculated increase in the recirculation region in the wake. Airfoil with DTE modification achieves the same lift coefficient at a lower incidence and thus at a lower drag coefficient, so that lift-to-drag ratio is increased in transonic cruise conditions compared to the original airfoil. The reduction in drag due to DTE modification is associated with weakening of shock strength and delay of shock which is greater than the increase in base drag.

• 대한기계학회논문집B
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• 제27권8호
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• pp.1097-1104
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• 2003

The current study analyzes Langmuir slip boundary condition theoretically and it is tested in practical numerical analysis for separation-associated flow. Slip phenomenon at the channel wall is properly implemented by various numerical slip boundary conditions including Langmuir slip model. Compressible backward-facing step flow is compared to other analysis results with the purpose of diatomic gas Langmuir slip model validation. The numerical solutions of pressure and velocity distributions where separation occurs are in good agreement with other numerical results. Numerical analysis is conducted for Reynolds number from 10 to 60 for a prediction of separation at T-shaped micro manifold. Reattachment length of flows shows nonlinear distribution at the wall of side branch. The Langmuir slip model predicts fairly the physics in terms of slip effect and separation.

• 한국전산유체공학회지
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• 제10권1호
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• pp.1-7
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• 2005

Three-dimensional numerical analysis of the flow around rectangular cylinders with various side ratios, D/H, from 0.2 to 2.0, was carried out for Reynolds number of 10³ by using a multi-directional finite difference method on a regular-arranged multi-grid. The predicted results are in good agreement with the experimental data. It is found that fluid dynamic characteristics of rectangular cylinders alternate between the high-pressure mode and the low-pressure mode of the base pressure for D/H=0.2-0.6. We show that this phenomenon is induced by the change of the flow pattern around rectangular cylinders.

• Journal of Mechanical Science and Technology
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• 제14권11호
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• pp.1257-1266
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• 2000

The flow field if a ship's propulsion mechanism of Weis-Fogh type is studied by the discrete vertex method. The wing in a channel is approximated by a finite number of bound vortices, and free vortices representing the separated flow are introduced from the trailing edge if the wing. The time histories of the thrust, the drag, and the moment acting on the wing are calculated, including the unsteady force due to the change of strength of the bound vortices. These calculated values agree well with the experimental values. The flow field of this propulsion mechanism is numerically clarified.

• Wind and Structures
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• 제18권5호
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• pp.529-548
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• 2014

This article presents the unsteady aerodynamic performance of crosswind stability obtained numerically for the ATM train. Results of numerical investigations of airflow past a train under different yawing conditions are summarized. Variations of occurrence flow angle from parallel to normal with respect to the direction of forward train motion resulted in the development of different flow patterns. The numerical simulation addresses the ability to resolve the flow field around the train subjected to relatively large yaw angles with three-dimensional Reynolds-averaged Navier-Stokes equations (RANS). ${\kappa}-{\varepsilon}$ turbulence model solved on a multi-block structured grid using a finite volume method. The massively separated flow for the higher yaw angles on the leeward side of the train justifies the use of RANS, where the results show good agreement with verification results. A method of solution is presented that can predict all aerodynamic coefficients and the wind characteristic curve at variety of angles at different speed.

• International Journal of Fluid Machinery and Systems
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• 제5권2호
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• pp.49-59
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• 2012

The present study is devoted to the influence of a superposed radial inflow in a rotor-stator cavity with a peripheral opening. The flow regime is turbulent, the two boundary layers being separated by a core region. An original theoretical solution is obtained for the core region, explaining the reason why a weak radial inflow has no major influence near the periphery of the cavity but strongly affects the flow behavior near the axis. The validity of the theory is tested with the help of a new set of experimental data including the radial and tangential mean velocity components, as well as three components of the Reynolds stress tensor measured by hot-wire anemometry. The theoretical results are also in good agreement with numerical results obtained with the Fluent code and experimental data from the literature.