• Transactions of the Korean Society of Mechanical Engineers B
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• v.25 no.3
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• pp.305-314
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• 2001

A modified model is proposed for calculation of transitional boundary layer flows. In order to develop the eddy viscosity model for the problem, the flow is divided into three regions; namely, pre-transition region, transition region and fully turbulent region. The pre-transition eddy-viscosity is formulated by extending the mixing length concept. In the transition region, the eddy-viscosity model employs two length scales, i.e., pre-transition length scale and turbulent length scale pertaining to the regions upstream and the downstream, respectively, and a universal model of stream-wise intermittency variation is used as a function bridging the pre-transition region and the fully turbulent region. The proposed model is applied to calculate three benchmark cases of the transitional boundary layer flows with different free-stream turbulent intensity (1%∼6%) under zero-pressure gradient. It was found that the profiles of mean velocity and turbulent intensity, local maximum of velocity fluctuations, their locations as well as the stream-wise variation of integral properties such as skin friction, shape factor and maximum velocity fluctuations are very satisfactorily predicted throughout the flow regions.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.803-810
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• 2017

the liquid oxygen transitions to a supercritical state, causing rapid changes in properties and pseudo boiling in supercritical combustion. the combustion reaction operating in a supercritical state depends on the turbulence diffusion caused by difference of density, therefore, a study of the diffusion flow and pseudo boiling is required. Many researchers have studied these phenomena in the supercritical combustion, but A case study by various variables is inadequate. In this study, the flow field and flame structure were investigated numerically by changing the recirculation flow and liquid oxygen core length through oxygen-fuel ratio(O/F), combustor diameter and recess ratio at supercritical pressure condition.

• Proceedings of the Korea Water Resources Association Conference
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• 2011.05a
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• pp.431-431
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• 2011

Rio Narcea 는 스페인 북부에 위치한 Astuias 지역을 흐르는 Nalon River 의 한 지류로서 총연장 102km 유역 면적 1,135 m이며. 사행천으로 홍수 시 범람하기 쉬운 곡류천의 특성상 잦은 홍수피해를 받고 있는 지역이다. 특히 2010년 6월에는 일주일 사이에 홍수 피해가 두 번씩이나 발생함에 따라 수많은 인명피해가 발생하였고 사회 SOC 시설이 큰 타격을 입는 등 상당한 피해를 야기하였다. 이에 1D 및 2D 수리 모델링 프로그램을 이용하여 사행천에 수리특성을 분석하고, 그에 따른 홍수범람도를 작성하여 1D와 2D 모델링을 비교분석하였고 이를 이용하여 홍수 피해 방지 대책을 마련하는데 도움이 되고자 한다. 1D 모델링은 HEC-GeoRAS 및 HEC-RAS를 이용하였으며, 2D 모델링에는 IBER를 이용하였다. Arc-GIS 툴을 이용한 HEC-GeoRAS 기능을 사용하여 강의 단면을 구성하고 HEC-RAS를 이용하여 1차원 모델링을 수행하였으며, 2D 모델링에는 스페인의 CIMNE에서 개발한 2차원 수리해석 프로그램인 IBER를 사용하였는데, 이 프로그램은 부정류 해석과 난류 해석, 유사이동 및 Dam-break 등의 해석이 가능하다. 1D 및 2D 모델링의 결과 값으로 얻어진 수심 및 유속을 토대로 1D는 Arc-GIS를 이용, 2D는 IBER 프로그램 내에 기능을 이용하여 바르셀로나에서 주로 사용되는 Catalan Water Agency 기준에 의한 홍수범람도를 작성하였다. 각각의 1D 와 2D 모델링으로 작성한 홍수범람도를 비교분석해 본 결과 거의 유사하게 표현됨을 알 수 있었으며, 두 모델링 기법 모두 홈수범람도를 표현함에 있어서 유용하게 사용될 수 있을 것이라 생각된다. 대상지역의 관련 자료의 유무에 따라 구분하여 1D 혹은 2D 모델링 기법을 선택 사용할 수 있으며. 유역의 홍수발생시 인명과 재산 피해에 대비한 홍수범람 지도 및 홍수재해지도 제작에 도움이 될 것으로 판단된다.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.35 no.1
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• pp.33-42
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• 2011

In this study, we investigated the natural convection on the outer surface of a vertical pipe by performing mass transfer experiments using fluids with high Pr number using the concept of analogy between heat and mass transfer. A cupric acid-copper sulfate electroplating system was adopted as the mass transfer system. Tests were performed for $Ra_H$ numbers from $1.4{\times}10^9$ to $4{\times}10^{13}$, Pr numbers from 2,094 to 4,173, and diameters from 0.005 m to 0.035 m. The test results for laminar flow conditions were in good agreement with the correlations reported by King, Jakob and Linke, McAdam, and Bottemanne, and those for turbulent conditions with the correlations presented by Fouad for a vertical plate and also proved the dependence on Pr numbers. The obtained correlations were $Nu_H=0.55Ra^{0.25}_H$ for laminar and $Nu_H=0.12Ra^{0.28}_HPr^{0.1}$ for turbulent. The transition between laminar and turbulent occurs at $Ra_H$ of about $10^{12}$.

• Tunnel and Underground Space
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• v.11 no.4
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• pp.319-327
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• 2001

Introduction of new design tools has been required to optimally design and operate the ventilation system of long vehicle tunnels.. The demand has led to wide spread use of the simulation technique throughout the would to analysis the dynamic relationship among the variables associated with vehicle tunnel ventilation. This paper aims at performing on-site study at local tunnels to test the applicability of NETVEN, a simulation model vehicle tunnel ventilation. The study was carried out at four urban as well as highway tunnels model of vehicle tunnel ventilation. The study was carried out at four urban as well as highway tunnels employing different ventilation systems as well as traffic methods. There were some discrepancies sound between the simulation output and measurements and the following four factors are considered to mainly cause those disagreement. (1) The real situation shows distinctive transient and retarding characteristics with respect to air flow and contaminant dispersion, while ventilation forces are not steady-state and in particular those traffic and climatic variables show significant instantaneous variation. (3) Near the exit portal, the CO levels show bigger differences. The general trend is that data with higher CO concentrations carry bigger discrepancies. Turbulent diffusion is though to be the main reason for it and also contribute to the fact hat the highest CO concentrations are found at the locations somewhat inward, not at the exit portals. (4) Higher traffic rate results in higher discrepancies of ventilation velocity. Along with the exhaust characteristics, the vehicle aerodynamic characteristics need to be studied continuously in order to reduce the velocity disagreement.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.38 no.7
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• pp.639-646
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• 2014

The comparative analysis of near-wall treatment methods that affect the prediction of heat transfer over the gas turbine nozzle guide vane were presented. To achieve this objective, wall-function and low Reynolds number methods, and the transition model were applied and simulated using NASA's C3X turbine vane. The predicted turbine vane surface pressure distribution data using the near-wall treatment methods were found to be in close agreement with experimental data. However, the predicted vane metal temperature and heat transfer coefficient displayed significant differences. Overall, the low Reynolds method and transition model did not offer specific advantages in the prediction of temperature and heat transfer than did the wall-function method. The Reynolds stress model used along with the wall-function method resulted in a relatively high accuracy of prediction of the vane metal temperature and heat transfer coefficient.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.10
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• pp.1-11
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• 2004

An experimental study was carried out to investigate the influence of flow conditions of a boundary layer on the near-wake of a flat plate. Various attaching positions of tripping wires were selected to change flow conditions on a boundary layer. Laminar, transitional, and turbulent boundary layer conditions at 0.98C from the leading edge are imposed to investigate the evolution of symmetric and asymmetric wake. An x-type hot-wire probe(55P61) is employed to measure at 8 stations of the near-wake region. Measured mean velocity distributions are presented in terms of similarity parameter. It is found that the symmetric wake collapses well to the universal profile in the central part of the wake. However, the universal profile is not suitable in describing an asymmetric wake.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.679-681
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• 2017

Numerical analysis was carried out by applying the concept of E-D(expansion-deflection) nozzle to dual bell nozzle. We used the CEA code to calculate the chemical composition of the nozzle and to analyze the freezing flow of 8 species. The turbulence model was chosen as the $k-{\omega}$ SST. We applied the concept of E-D nozzle to the dual bell nozzle and performed the calculated transition altitude and performance. As a result of the interpretation, the application of the E-D nozzle concept led to the formation of over-expansion conditions, which resulted in an increase in the transition altitude.

• Tunnel and Underground Space
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• v.12 no.4
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• pp.277-283
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• 2002

This experimental study concerns the characteristics of a helical flow in a concentric annulus with a diameter ratio of 0.52, whose outer cylinder is stationary and inner one is rotating. The pressure losses and skin friction coefficients have been measured for the fully developed flow of Non-Newtonian fluid, aqueous solution of sodium carbomethyl cellulose (CMC) and bentonite with inner cylinder rotational speed of 0~400 prm. Also, the visualization of helical flows has been performed to observe the unstable waves. The results of present study reveal the relation of the Reynolds number Re and Rossby number Ro with respect to the skin friction coefficients. In somehow, they show the existence of flow instability mechanism. The pressure losses increase as the rotational speed increases, but the gradient of pressure losses decreases as the Reynolds number increases in the regime of transition and turbulence. And the increase of flow disturbance by Taylor vortex in a concentric annulus with rotating inner cylinder results in the decrease of the critical Reynolds number with the increase of skin friction coefficient.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.25 no.6
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• pp.786-798
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• 2001

This paper describes the phenomena of wake-induced transition of the boundary layers on a NACA0012 airfoil using measured phase-averaged data. Especially, the phase-averaged wall shear stresses are reasonably evaluated using the principle of Computational Preston Tube Method. Due to the passing wake, the turbulent patch is generated in the laminar boundary layer on the airfoil and the boundary layer becomes temporarily transitional. The patches propagate downstream with less speed than free-stream velocity and merge with each other at further down stream station, and the boundary layer becomes more transitional. The generation of turbulent patch at the leading edge of the airfoil mainly depends on velocity defects and turbulent intensity profiles of passing wakes. However, the growth and merging of turbulent patches depend on local streamwise pressure gradients as well as characteristics of turbulent patches. In this transition process, the present experimental data show very similar features to the previous numerical and experimental studies. It is confirmed that the two phase-averaged mean velocity dips appear in the outer region of transitional boundary layer for each passing cycle. Relatively high values of the phase-averaged turbulent fluctuations in the outer region indicate the possibility that breakdown occurs in the outer layer not near the wall.