• Proceeding of EDISON Challenge
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• 2012.04a
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• pp.81-84
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• 2012

항공기 설계에서 중요한 해석 대상중의 하나인 에어포일 NACA 4412 형상을 2차원 난류 점성유동으로 접근하여 일정 받음각에 따른 유동 현상을 실험 결과와 비교해 보았다. 또한, 역압력구배, 유동 박리, 와류 등의 현상이 어디에서 어떻게 생성되는지 해석을 통하여 분석해 보았다.

• Proceedings of the Korean Nuclear Society Conference
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• 1998.05a
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• pp.603-608
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• 1998

유체내의 물체 주위에서 유동박리로 인해 생성되는 와류쉐딩은 열전달이나 물질전달을 촉진시키는 이점이 있으나, 항력을 증가시키거나 유동 및 온도의 요동에 의해 구조물을 손상시키는 단점이 있다. 특히 물체와 주위 유동 사이에 공진이 일어나면 항력값이 증가하면서 항력과 양력의 진폭이 급격히 증가하여 물체에 심각한 손상을 초래할 수 있다. 본 연구에서는 레이놀즈수 200 이하의 층류유동에서 공진시 물체 주위의 유동현상과 이로 인한 양력과 항력의 변화들을 수치해석방법을 통하여 분석하였다 수치해석은 일반좌표계에서 유한체적법을 적용하여 Navier-Stokes 방정식을 차분화하였다. 이때 방정식의 종속변수로는 공변속도를 채택하였으며, 이산화된 방정식은 분리단계법을 이용하여 수치해를 구하였다. 입구유속의 강제진동에 의한 사각실린더 주위의 와류쉐딩시 공진이 발생하는 강제진동수의 범위는 원통실린더의 경우와 유사하였으나 상대적으로 폭이 더 좁았다 그리고 공진이 발생하는 강제진동수의 범위는 진폭이 증가할수록 증가하였다. 쉐딩 진동수가 일정하면서 입구유속의 진폭이 증가하면 이에 비례하여 실린더 주위의 유속이 상대적으로 증가하게 되어 와도가 강해지면서 입추유속 진폭에 비례하여 항력의 평균값 뿐 아니라 항력과 양력의 진폭도 증가하였다. 그리고 실린더 뒷면의 와류 생성영역은 진폭에 비례하여 감소하였다. 진폭의 변화에 따라 상변화가 서로 상이한 것은 실린더 뒤쪽의 와류들이 상하면의 합력차이를 변화시켰고 이것이 진폭변화에 따라 상변화를 상이하게 나타나게 한 원인으로 진폭이 클수록 실린더 뒤쪽에서 압력변화가 심하게 변하면서 실린더 앞쪽까지 더 많은 영향을 미쳤기 때문이다.선원의 사용자에게 제공되는 최종방사능을 평가하는데 유용하게 사용될 수 있다.r의 분포를 보였다.cting the effect of earthquake on structures. This paper is based on the presented paper at the Bertero Symposium held in January 31an4 February 1 at Berkeley, California, USA which was entitled "Needs to Evaluate Real Seismic Performance of Buildings-Lessons from 1995 Hyogoken-Nambu Earthquake-". The lessons for buildings from the damage due to the Hyogoken-Nambu Earthquake are necessity to develop more rational seismic design codes based upon a performance-based design concept, and to evaluate seismic performance of existing buildings. In my keynote lecture at the Korean Association for Computational Structural Engineering, the history of seismic design and use of structural analysis in Japan, the lessons for buildings from the Hyogoken-Nambu Earthquake, the

• Journal of the Korean Society of Marine Environment & Safety
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• v.25 no.6
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• pp.795-801
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• 2019

The aim of this study was to investigate the possibility of the skin-friction reduction by vortex control. A vortical system such as a horseshoe vortex, a hairpin vortex, and a wake region was induced around a hemisphere attached on a Perspex flat plate in the circulating water channel. Hairpin vortices were developed from the wake region and horseshoe vortices were formed by an adverse pressure gradient in front of the hemisphere. The horseshoe vortices located on the flank of the hemisphere induced a high momentum flow in the wake region by the direction of their vorticity. This process increased the frequency of the hairpin vortices as well as the frictional drag on the surface of the wake region. To reduce the skin-friction drag, suction control in front of the hemisphere was applied through a hole. Flow visualization was performed to optimize the free-stream velocity, size of the hemisphere, and size of the suction hole. Once the wall suction control mitigated the strength of the horseshoe vortex, the energy supplied to the wake region was reduced, causing the frequency of the hairpin vortex generation to decrease by 36.4 %. In addition, the change in the skin-friction drag, which was measured with a dynamometer connected to a plate in the wake region, also decreased by 2.3 %.

• Proceedings of the KSME Conference
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• 2005.11a
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• pp.74.1-74.1
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• 2005

• Journal of the Korean Society of Marine Environment & Safety
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• v.24 no.1
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• pp.92-100
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• 2018

Vortical systems are considered a main feature to sustain turbulence in a boundary layer through interaction. Such turbulent structures result in frictional drag and erosion or vibration in engineering applications. Research for controlling turbulent flow has been actively carried out, but in order to show the effect of vortices in a turbulent boundary layer, it is necessary to clarify the mechanism by which turbulent energy is transferred. For this purpose, it is convenient to demonstrate and capture phenomena in a laminar boundary layer. Therefore, in this study, the interactions of disturbed flow around a hemisphere on a flat plate in laminar flow were analyzed. In other words, a street of hairpin vortices was generated following a wake region formed after flow separation occurred over a hemisphere. Necklace vortices surrounding the hemisphere also appeared due to a strong adverse pressure gradient that brought high momentum fluid into the wake region thereby leading to an increase in the frequency of hairpin vortices. To mitigate the effect of these necklace vortices, local suction control was applied through a hole in front of the hemisphere. Flow visualization was recorded to qualitatively determine flow modifications, and hot-film measurements quantitatively supported conclusions on how much the power of the hairpin vortices was reduced by local wall suction.

• The Journal of the Acoustical Society of Korea
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• v.40 no.4
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• pp.261-269
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• 2021

Without any validation of the incompressible assumption, most of previous studies on cavitation flow and its noise have utilized numerical methods based on the incompressible Reynolds Average Navier-Stokes (RANS) equations because of advantage of its efficiency. In this study, to investigate the effects of the flow compressibility on the Tip Vortex Cavitation (TVC) flow and noise, both the incompressible and compressible simulations are performed to simulate the TVC flow, and the Ffowcs Williams and Hawkings (FW-H) integral equation is utilized to predict the TVC noise. The DARPA Suboff submarine body with an underwater propeller of a skew angle of 17 degree is targeted to account for the effects of upstream disturbance. The computation domain is set to be same as the test-section of the large cavitation tunnel in Korea Research Institute of Ships and Ocean Engineering to compare the prediction results with the measured ones. To predict the TVC accurately, the Delayed Detached Eddy Simulation (DDES) technique is used in combination with the adaptive grid techniques. The acoustic spectrum obtained using the compressible flow solver shows closer agreement with the measured one.

• Proceeding of EDISON Challenge
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• 2016.03a
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• pp.638-642
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• 2016

현재 양력발생의 원리는 긴 경로 이론과 동시 통과 이론 등으로 알려져 있으며, 이 이론들은 간단히 설명하려는 목적으로 인해 양력발생의 원리가 와전되어왔다. 본 연구에서는 여러 양력발생의 원리 중 Kutta-Joukowski의 이론을 이용하여 순환을 통한 양력발생의 관계에 대해 연구를 수행하였다. 해석 모델은 대칭형 에어포일인 NACA0012를 이용하였다. 해석 프로그램으로는 EDISON을 이용하였으며 시간에 따른 와도를 확인하기 위해 비정상상태 해석을 진행하였다. 그 결과 유동이 시간의 경과에 따라 에어포일 뒷전으로 밀려나면서 Kutta-Joukowski의 이론에 중요한 논점인 출발 와류가 생성됨을 확인할 수 있었다. 이로 인해 순환이 형성되어 양력이 발생함을 추측할 수 있다. 추가적으로 받음각과 출발 와류 사이의 영향성을 연구하였다. 받음각이 커짐에 따라 출발 와류가 에어포일 뒷전에서 더 크게 발생하였고, 받음각이 낮아질수록 출발 와류의 진행이 가속화됨을 확인할 수 있었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.5
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• pp.405-412
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• 2012

A flow control on airfoil installed a vortex cell for high efficiency wind turbine blade in stationary and dynamic stall conditions have been numerically investigated by solving the compressible Navier-Stokes equations. The numerical scheme is based on a node-based finite-volume method with Roe's flux-difference splitting and an implicit time-integration method coupled with dual time step sub-iteration. The computed result for the airfoil in the stationary showed that lift-drag ratio increases due to low pressure by the vortex cell. The oscillating airfoil with the vortex cell showed that the magnitude of hysteresis loop is reduced due to the enhanced vortex in the cell.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.4
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• pp.336-343
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• 2009

Secondary flow losses can be as high as 30~50% of the total aerodynamic losses generated in the cascade of a turbine. Therefore, these are important part for improving a turbine efficiency. As well, many studies have been performed to decrease the secondary flow losses. The present study deals with the leading edge fences on a wing-body to decrease a horseshoe vortex, one of the factors to generate the secondary flow losses, and investigates the characteristics of the generated horseshoe vortex as the shape factors, such as the installed height, and length of the fence. The study was investigated using $FLUENT^{TM}$. Total pressure loss coefficient was improved about 4.0 % at the best case than the baseline.

• Journal of the Korean Society of Propulsion Engineers
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• v.13 no.2
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• pp.26-34
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• 2009

Secondary flow losses can be as high as 30~50% of the total aerodynamic losses for a turbo-machinery blade or stator row. These are important part for improving a turbine efficiency. Therefore, many studies have been performed to decrease the secondary flow losses. The present study deals with the chamfered leading-edge at a generic wing-body junction to decrease the horseshoe vortex, one of factors to generate the secondary flow losses, and investigates the vortex generation and the characteristics of the horseshoe vortex with the chamfered height, and depth of the chamfer by using $FLUENT^{TM}$. It was found that the total pressure loss for the best case can be decreased about 1.55% compare to the baseline case.