• 해양환경안전학회지
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• 제12권4호
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• pp.261-266
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• 2006

이 연구에서는 실제선박의 후드룸을 1/15로 축소한 비대칭 입출구를 갖는 장방형 모델을 대상으로 가시화 실험을 수행하고 내부의 유동 특성을 고찰하고자 하였다. 속도장의 계측은 CACTUS'2000을 이용한 2차원 PIV기법으로 하였으며 4개의 계측영역을 설정하여 계측한 결과 유동장의 환기구조를 지배하는 흐름은 유동장의 좌측 벽면의 흡기구로부터 대각방향의 우측상부로 흐르는 나선형의 'L'형 유동이었다. 또한 주 흐름의 영향으로 유동장의 중앙부분에 강제와류형태의 재순환 흐름이 존재하였다.

• 한국전산유체공학회지
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• 제18권1호
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• pp.28-35
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• 2013

Behavior of the side force generated at high angles of attack by two ogive-cylinder bodies of revolution with nose fineness ratio of 2.3 (B1) and 3.5 (B2) and the effect of a strip placed close the nose tip of each body (B1S and B2S) are analyzed through the wind tunnel test at ReD=200,000 and a=42~60 deg. The side force generated by B1 is increased by placing a strip. The side force generated by B2 is in the starboard direction and its magnitude is higher than that of the B1S. The effect of the strips with various dimensions placed on B2 is investigated. It is found that the 4-layer strip placed on the starboard reversed the direction of the side force into port direction. It is confirmed by numerical simulations that the strip promotes the flow separation and increases the average pressure on the side where it is placed and consequently produces the side force in the corresponding direction.

• 한국해양학회지
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• 제30권4호
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• pp.355-364
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• 1995

f-plane 혹은 $\beta$-plane을 갖고 강체 회전중인 균질수에 외부로부터 고밀도의 유체 를 계속 주입시 주입된 고밀도 류의 확장형태와 이와 대응하는 기존의 균질수(상층수) 의 흐름을 관찰하였다. 고밀도류는 주입후 편향력에 의해 서안을 따라 흐르면서 내부 로 침투 확장하여 회전축에 비대칭인 모양을 보인다. 특히 $\beta$-plan에서는 바닥 경사도 의 증가에 따른 압력 경도력의 증가에 의한 서안을 따라 흐르는 속도가 증가되고 결국 편향력의 증가로 서안에서의 폭이 f-plane보다 좁게 나타난다. 그러나 남쪽에 이르러 서는 유입수의 국지적인 두께증가로 인해 확장 속도가 동시에 경계면상에서 의 혼합을 유발시키기도 한다. 유입된 고밀도류의 상층의 와도발생과 관련한 역할은 확장경로상 의 국지적인 지형효과의 유발과 유입으로 인한 상층수의 수직운동, 즉 vortex-tube stretching 효과를 발생시키는 것으로 볼 수 있으나 f-plane의 경우는 후자에 해당하 는 반시계 방향의 축대칭류를 생성시킴으로써 지형효과는 서안 경계층에만 존재하는 것으로 관찰되었으며 이때의 지형효과는 북향의 매우 약한 서안 경계류로 나타나고 있 다. 한편 $\beta$-plan에서 의 유입수의 역할은 실험면적의 동쪽반인 내부흐름에서는 h보다 는 dh/SUB $\beta$/dt의 크기가 우세하여 결국 상대와도의 감소경향인 시계방향의 음의 와 도(negative vorticity)의 발생과 서쪽반에서는 경계면의 경사 (tilting)에 의한 지형 효과가 극대화되어 유입수의 방향과 정반대인 강한 흐름이 나타나고 있다.

• 한국항공우주학회지
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• 제31권2호
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• pp.17-24
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• 2003

본 논문은 $65^{\circ}$ 후퇴각을 갖는 삼각날개에 대하여 뿌리시위를 기준으로 한 레이놀즈수 $1.76{\times}10^6$에서 정상 풍동실험에 의한 결과를 보였다. 풍동실험은 총 188개의 압력공과 다채널 데이터 처리 시스템을 사용하여 날개 윗면에서의 압력 분포를 측정하였다. 날개 윗면에서의 압력분포의 분석으로부터 옆미끄럼각과 받음각이 날개의 공력 특성에 미치는 복합적인 영향에 대한 직관을 얻을 수 있었다. 옆미끄럼각이 있는 경우, 바람쪽 날개의 와류강도는 바람 반대쪽 날개의 화류강도보다 훨씬 강하였다. 이와 같은 좌우 날개의 비대칭적인 압력분포로 인하여 음의 롤링모멘트가 발생하였다. 하지만, 일정 범위의 받음각과 옆미끄럼각(${\alpha}$=$24^{\circ}{\sim}36^{\circ}C$, ${\beta}$=$-5^{\circ}{\sim}-15^{\circ}C$)에서는 롤링모멘트의 방향이 갑자기 바뀌는 롤링모멘트 역전현상을 관찰할 수 있었다.

• Steel and Composite Structures
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• 제34권5호
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• pp.699-713
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• 2020

The aerodynamic performance of long-span cable-stayed bridges is much dependent on its geometrical configuration and countermeasure strategies. In present study, the aerodynamic performance of three composite cable-stayed bridges with different tower configurations and passive aerodynamic countermeasure strategies is systematically investigated by conducting a series of wind tunnel tests in conjunction with theoretical analysis. The structural characteristics of three composite bridges were firstly introduced, and then their stationary aerodynamic performance and wind-vibration performance (i.e., flutter performance, VIV performance and buffeting responses) were analyzed, respectively. The results show that the bridge with three symmetric towers (i.e., Bridge I) has the lowest natural frequencies among the three bridges, while the bridge with two symmetric towers (i.e., Bridge II) has the highest natural frequencies. Furthermore, the Bridge II has better stationary aerodynamic performance compared to two other bridges due to its relatively large drag force and lift moment coefficients, and the improvement in stationary aerodynamic performance resulting from the application of different countermeasures is limited. In contrast, it demonstrates that the application of both downward vertical central stabilizers (UDVCS) and horizontal guide plates (HGP) could potentially significantly improve the flutter and vortex-induced vibration (VIV) performance of the bridge with two asymmetric towers (i.e., Bridge III), while the combination of vertical interquartile stabilizers (VIS) and airflow-depressing boards (ADB) has the capacity of improving the VIV performance of Bridge II.

• 대한기계학회논문집B
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• 제29권6호
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• pp.737-746
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• 2005

The present study investigates heat/mass transfer and flow characteristics in a ribbed rotating passage with turning region. The duct has an aspect ratio (W/H) of 0.5 and a hydraulic diameter ($D_h$) of 26.67 mm. Rib turbulators are attached in the cross arrangement on the leading and trailing surfaces of the passage. The ribs have a rectangular cross section of $2\;mm\;(e){\times}\;mm\;(w)$ and an attack angle of $70^{\circ}$. The pitch-to-rib height ratio (p/e) is 7.5, and the rib height-to-hydraulic diameter ratio ($e/D_h$) is 0.075. The rotation number ranges from 0.0 to 0.20 while the Reynolds number is constant at 10,000. To verify the heat/mass transfer augmentation, internal flow structures are calculated for the same conditions using a commercial code FLUENT 6.1. The heat transfer data of the smooth duct for various Ro numbers agree well with not only the McAdams correlation but also the previous studies. The cross-rib turbulators significantly enhance heat/mass transfer in the passage by disturbing the main flow near the surfaces and generating one asymmetric cell of secondary flow skewing along the ribs. Because the secondary flow is induced in the first-pass and turning region, heat/mass transfer discrepancy is observed in the second-pass even for the stationary case. When the passage rotates, heat/mass transfer and flow phenomena change. Especially, the effect of rotation is more dominant than the effect of the ribs at the higher rotation number in the upstream of the second-pass.

• 대한방사선기술학회지:방사선기술과학
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• 제25권1호
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• pp.55-62
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• 2002

Aneurysm-mimicking findings were frequently visualized due to hemodynamical causes of dephasing effects around area of A-com artery during magnetic resonance angiography(MRA) and these kind of phenomena have not been clearly known yet. We investigated the hemodynamical patterns of dephasing effect around area of the A-com artery that might be a cause of false intracranial aneurysms on MRA. For experimental study, We used hand-made silicon phantoms of the asymmetric A-com artery as like a bifurcation configuration. In a closed circulatory system with UHDC computer driven cardiac pump system. MRA and fast digital subfraction angiography(DSA) involved the use of these phantoms. Flow patterns were evaluated with axial and coronal imaging of MRA(2D-TOF, 3D-TOF) and DSA of Phantoms constructed from an automated closed-type circulatory system filled with glycerol solution [circulation fluid(glycerol:water = 1:1.4)]. These findings were then compared with those obtained from computational fluid dynamic(CFD) for inter-experimental correlation study. Imaging findings of MRA, DSA and CFD on inflow zone according to the following: a) MRA demonstrated high signal intensity zone as inflow zone on silicon phantom; b) Patterns of DSA were well matched with MRA on trajectory of inflow zone; and c) CFD were well matched with MRA on the pattern of main flow. Imaging findings of MRA. DSA and CFD on turbulent flow zone according to the following: a) MRA demonstrated hyposignal intensity zone at shoulder and axillar zone of main inflow; b) DSA delineated prominent vortex flow at the same area. The hemodynamical causes of signal defect, which could Induce the false aneurysm on MRA, turned out to be dephasing effects at axilla area of bifurcation from turbulent flow as the results of MRA, DSA and CFD.

• 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.