• 대한기계학회논문집B
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• 제30권4호
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• pp.298-305
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• 2006

The flow around a circular cylinder which oscillates rotationally with a relatively high forcing frequency has been investigated experimentally using flow visualization and hot-wire measurements. Dominant parameters are Reynolds number (Re), oscillation amplitude $({\theta}_A)$, and frequency ratio $F_R=f_f/f_n$, where $f_f$ is the forcing frequency and $f_n$ is the natural frequency of vortex shedding. Experiments were carried out under the conditions of $Re=4.14{\times}10^3,\;{\theta}_A={\pi}/6$, and $0{\leq}F_R{\leq}2$. The effect of frequency ratio $F_R$ on the flow structure of wake was evaluated by measuring wake velocity profile and spectral analysis of hot-wire signal. Depending on the frequency ratio $F_R$, the cylinder wake has 5 different flow regimes. The vortex formation length and vortex shedding frequency are changed significantly before and after the lock-on regime. The drag coefficient was reduced under the condition of $F_R<1.0$ and the maximum drag reduction is about 33% at $F_R=0.8$. However, the drag is increased as $F_R$ increases beyond $F_R=1.0$. This active flow control method can be effective in aerodynamic applications, if the forcing parameters are selected optimally.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2008년도 춘계학술대회논문집
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• pp.193-196
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• 2008

The vortical structures in a turbulent boundary layer (TBL) developed over a flat plate have been investigated experimentally. The flow conditions tested in this study were Re$_{\theta}$ = 3700, Re$_{\delta}$ = 11${\times}$105 and the shape factor H = 1.3. Instantaneous velocity fields in the streamwise-wall-normal planes were measured by using a dynamic PIV system. A trip-wire and sandpapers were placed behind the leading edge to promote the turbulent transition. 1000 velocity fields were obtained consecutively with a time interval of 1 millisecond. Streamwise u-velocity components were temporally averaged in the measuring plane. In addition, 2000 velocity fields were obtained randomly and ensemble-averaged to get the fully-developed turbulent characteristics. Profiles of the normalized u-component, turbulent intensities and Reynolds shear stress were evaluated. The structures of spanwise vortices were extracted from the instantaneous velocity fields by determining the swirling strength, ${\lambda}_{ci}$. The wall-normalized locations of vortices were temporally averaged in the measuring plane with respect to their rotational direction. The correlations between the temporally averaged u and the temporally averaged $y^+$ of vortices were evaluated. For the case of positive vortices, the correlation is not significant. However, the negative vortices show a strong negative correlation. The y-location of negative vortices tends to increase, as the averaged u decreases and vice versa. These findings indicate that the number of negative vortices in the outer layer increases during the outward bursting events.

• Journal of Advanced Marine Engineering and Technology
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• 제35권2호
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• pp.264-270
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• 2011

본 연구는 직렬배열 상태에 놓인 3원주 주위의 유동장 특성을 PIV를 이용하여 파악한 것이다. 실험은 레이놀즈수 Re=$3.0{\times}10^3{\sim}5.0{\times}10^3$ 범위 내에서 수평간격비(P/D)를 P/D=1.25~3.75로 변화시켜가며 행하였다. 각각의 실험 파라메터에서 Strouhal 수, 와도변화, 순간 및 평균 속도벡터 및 속도분포를 측정하였으며 그 결과를 요약하면 다음과 같다. 3번째 원주 후방에서 측정한 Strouhal 수는 수평간격비 P/D에 따라 크게 3가지 영역으로 구분되며, 각 원주의 후류에서의 흐름 패턴은 이들 영역에 따라 달랐다. 각 원주 후방에서 시간평균 흐름은 거의 정체상태에 있었으며, 그 정체영역의 크기는 1번째, 2번째, 3번째 원주 순으로 작았다. 2번째 원주 전, 후방 영역에서는 받음각 미소 (${\alpha}= {\pm}5^{\circ}$)에 따라 서로 반대방향의 볼텍스가 형성했다.

• Environmental Engineering Research
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• 제25권4호
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• pp.498-505
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• 2020

This study analyzes the velocity and pressure incurred by protruding shapes installed within the inlet part of a pressurized membrane module during operation to determine the fluid flow distribution. In this paper, to find the flow distribution within a module, it investigates the velocity and pressure values at cross-sectional and outlet planes, and 9 sections classified on outlet plane using computational fluid dynamics. From the Reynolds number (Re), the fluid flow was estimated to be turbulent when the Re exceeded 4,000. In the vertical cross-sectional plane, shape 4 and 6 (round-type protrusion) showed the relatively high velocity of 0.535 m/s and 0.558 m/s, respectively, indicating a uniform flow distribution. From the velocity and pressure at the outlet, shape 4 also displayed a relatively uniform fluid velocity and pressure, indicating that fluid from the inlet rapidly and uniformly reached the outlet, however, from detailed data of velocity, pressure and flowrate obtained from 9 sections at the outlet, shape 6 revealed the low standard deviations for each section. Therefore, shape 6 was deemed to induce the ideal flow, since it maintained a uniform pressure, velocity and flowrate distribution.

• 한국가시화정보학회지
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• 제16권1호
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• pp.30-36
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• 2018

In the present study, we investigate the flow characteristics of a quadrotor UAV in a hovering mode by measuring multiple two-dimensional velocity fields in the wake. The experiment is conducted at Re = 24,000 in a chamber large enough to neglect the ground effect, where Re is the Reynolds number based on the rotor chord length and the rotor tip speed. The rotational speed of the rotor is determined by an optical tachometer so that the lift force can be balanced with the weight of the UAV. The velocity field measured on the center plane of the rotor shows that the vortices are shedding from the tip of the rotor, inducing large fluctuations in the streamwise velocity along the wake shear layer. The strength of the rotor-tip vortex shedding is asymmetric with respect to the rotor axis due to the interaction between the rotor and the wake centerline of each rotor is inclined to the center of the UAV due to the pressure difference caused by the induced velocity. The wake from each rotor moves closer to each other while traveling in the streamwise direction, and then is merged together inducing large fluctuations in the transverse velocity. Due to the wake merging, on the center plane of the UAV, the velocity increases in the streamwise direction showing two-peak structure in the streamwise velocity contours.

• 한국항공우주학회지
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• 제44권6호
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• pp.477-483
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• 2016

본 연구는 Particle Image Velocimetry(PIV) 기법을 이용하여 마하수 2.96의 평판에 대해 층류, 천이, 난류 경계층의 속도 분포를 측정하였다. Schlieren 가시화 기법과 PIV 기법을 이용하여 앞전에서 발생한 경사 충격파가 평판 위의 유동장에 영향을 주는지 확인하였다. 층류 경계층의 경우, 실험에서 측정한 속도 분포가 압축성 Blasius 속도 분포를 만족하였다. 천이 경계층의 속도 분포는 벽면 부근부터 이론적인 난류 속도 분포로 변했으며, Re = $1.41{\times}10^6$에서 천이가 시작되었다. 난류 경계층 영역에서는 압축성 효과를 고려한 Van Driest 변환 속도가 비압축성 로그 법칙을 만족하였다. 또한 로그 구간이 끝나는 위치($y/{\delta}{\approx}0.28$)가 비압축성 난류 경계층($y/{\delta}{\approx}0.2$)에 비해 벽면에서 더 멀어진 것을 확인하였다.

• 한국항공우주학회지
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• 제33권1호
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• pp.54-61
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• 2005

기체와 액체 추진제를 사용하는 동축형 분사기의 분무특성을 조사하기 위하여 shadow graph와 mechanical patternator, PDPA를 이용한 실험을 수행하였다. 차원해석 방법을 도입하여 운동량 플럭스 비(M)와 레이놀즈 수(Re)를 기체/액체 동축형 분무의 주요 변수로 설정하였고, 실험을 통하여 전단 및 스월 동축형 분무의 특성을 거시적 및 미시적 관점에서 비교분석하였는데, 기체 추진제의 영향력이 커지는 분사조건에서 전단 및 스월 동축형 분무의 거시적 특성이 유사해짐을 확인할 수 있었다. 또한, 본 연구에서는 미시적 분무특성에 대한 분석 결과로서 분무액적 크기와 분사조건 사이의 관계식도 제시하였다.

• 대한조선학회논문집
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• 제49권5호
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• pp.440-446
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• 2012

A twisted cylinder has been newly designed by rotating the elliptic cross section along the spanwise direction in order to reduce the drag and vorticies in wake region. The flow around the twisted cylinder at a subcritical Reynolds number (Re) of 3000 is investigated to analyze the effect of twisted spiral pattern on the drag reduction and vortex suppression using large eddy simulation (LES). The instantaneous wake structures of the twisted cylinder are compared with those of a circular and a wavy cylinder at the same Re. The shear layer of the twisted cylinder covering the recirculation region is more elongated than that of the circular and the wavy cylinder. Successively, vortex shedding of the twisted cylinder is considerably suppressed, compared with those of the circular and the wavy cylinder. Consequently, the mean drag coefficient and the fluctuating lift of the twisted cylinder are less than those of the circular and the wavy cylinder.

• 대한기계학회논문집A
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• 제29권10호
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• pp.1289-1297
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• 2005

The flow in a microchannel is usually characterized as a low Reynolds number (Re) so that good mixing is quite difficult to be achieved. In this regard, we developed a novel chaotic micromixer, named Serpentine Laminating Micromixer (SLM) in the present study, Part 1. In the SLM, the higher level of chaotic mixing can be achieved by combining two general chaotic mixing mechanisms: splitting/recombination and chaotic advection. The splitting and recombination (in other term, lamination) mechanism is obtained by the successive arrangement of 'F'-shape mixing units in two layers. The chaotic advection is induced by the overall three-dimensional serpentine path of the microchannel. Chaotic mixing performance of the SLM was fully characterized numerically. To compare the mixing performance, a T-type micromixer which has the same width, height and length of the SLM was also designed. The three-dimensional numerical mixing simulations show the superiority of the SLM over the T-type micromixer. From the cross-sectional simulation results of mixing patterns, the chaotic advection effect from the serpentine channel path design acts favorably to realize the ideal lamination of fluid flow as Re increases. Chaotic mixing mechanism, proposed in this study, could be easily integrated in Micro-Total-Analysis-System, Lab-on-a-Chip and so on.

• 전자공학회논문지SC
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• 제42권1호
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• pp.33-37
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• 2005

마이크로믹서는 Bio-MEMS 혹은 μ-TAS 분야에서 중요한 역할을 수행한다. 혼합은 두 유체의 난류 상태와 상호확산에 의해 발생된다. 마이크로채널 내에서는 레이놀즈수가 작기 때문에 (Re << 2000) 난류가 발생되기 어려우므로 주로 상호확산에 의해서만 혼합된다. 따라서 두 유체가 적정하게 혼합되기 위해서는 긴 채널이 요구된다. 본 논문에서는 혼합에 소요되는 길이를 줄이기 위해서 PMN-PT에 의해 발생된 초음파에 의해 혼합되는 새로운 믹서를 제안하였다. 챔버 내에 발생된 초음파는 두 유체에 의해 생성된 경계면과 수직한 방향으로 방사된다. 사용된 두 유체는 상하방향으로 경계층을 이룬다. 혼합 상태는 NaOH와 페놀프탈렌의 반응에 따른 색상 변화론 관찰하여 측정하였다.