• 한국항공우주학회지
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• 제47권1호
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• pp.17-25
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• 2019

항공기의 Intake는 공간적 제약 또는 생존성 확보의 이유로 S형태의 곡률을 갖는 덕트를 가진다. 그러나 덕트의 곡률은 2차유동과 유동박리의 발생을 야기하며 불균일한 압력분포 생성의 원인이 된다. 본 연구에서는 RAE M 2129 S-Duct의 형상에 보조 Duct를 적용하여 경계층 흡입을 수행하였다. 경계층 흡입의 위치와 각도를 설계변수로 설정하였으며, 흡입면에서 동일 유량을 흡입하는 조건을 부여하였다. S-Duct의 전산해석 타당성을 검증하기 위하여 Port Side와 Starboard Side의 무차원 압력 분포를 ARA 실험값, 전산해석 값과 각각 비교하여 확인하였다. 본 연구에서는 유동 왜곡을 판단하는 공기역학적 성능인자로 유동 왜곡 계수를 사용 하였으며, 경계층 흡입에 의한 유동박리, 와류, 유량 분포 및 압력 분포를 비교 분석 하였다. 그 결과 경계층 흡입 적용 이전과 비교하여 최대 26.14%의 유동 왜곡 계수 저감 효과를 확인하였다.

• 농업과학연구
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• 제36권1호
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• pp.87-98
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• 2009

대전 3대 하천의 하나인 갑천의 유등천 합류전 지점의 하천유지유량 확보를 위해 상류 유역에 금곡지와 괴곡지를 각각 설치하는 경우 각각 장안지, 방동지의 기존 저수지를 포함하여 직렬, 병렬 연계 운영을 반영하여 목표 지점의 유량을 1966년부터 2007년까지 모의하여 효과를 분석한 결과 다음과 같다. 첫째, 방동지-금곡지 직렬 연계에 의해 금곡지로부터 용수공급능력을 분석한 결과 연평균하여 하천유지유량 공급량은 6.83백만 $m^3$, 용수공급량/유역면적은 403.4 mm, 단위유역 용수공급량/강우량 비율은 33.0 %, 용수공급량/유입량 비율은 96.4 %, 용수공급량/저수량 비율은 81.9 %, 유입량/저수량 비율은 112.3 %였다. 둘째, 장안지-금곡지 병렬 연계를 고려한 갑천지점의 유량을 분석한 결과 유황은 연평균하여 풍수량 $4.806m^3/s$, 평수량 $2.217m^3/s$, 저수량 $1.140m^3/s$, 갈수량 $0.887m^3/s$로 분석되었으며, 평균갈수량은 목표유량 $1.486m^3/s$보다 $0.599m^3/s$ 적게 나타났다. 셋째, 장안지-방동지 병렬 연계에 의해 괴곡지 유입량을 모의하였고, 괴곡지로부터 용수공급능력을 분석한 결과 연평균하여 하천유지유량 공급량은 49.60백만 $m^3$, 용수공급량/유역면적은 246.5 mm, 단위유역 용수공급량/강우량 비율은 19.4 %, 용수공급량/유입량 비율은 40.8 %, 용수공급량/저수량 비율은 412.1 %, 유입량/저수량 비율은 1,189.8 %였다. 넷째, 괴곡지 방류를 고려한 갑천 지점의 유량을 분석한 결과 유황은 연평균하여 풍수량 $4.501m^3/s$, 평수량 $2.277m^3/s$, 저수량 $1.743m^3/s$, 갈수량 $1.564m^3/s$로 분석되었으며, 평균갈수량은 목표유량 $1.486m^3/s$보다 $0.078m^3/s$ 높게 나타났다. 요약하면 괴곡지를 설치하는 것이 금곡지를 설치하는 것보다 갑천 지점의 하천유지유량을 확보하는데 효율성이 높은 것으로 분석되었다.

• 한국정밀공학회지
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• 제30권12호
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• pp.1295-1301
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• 2013

The cause of flow mark defect is known as non-uniform temperature of mold surface when the flow front meets the cold cavity. The exact definition and classification of Flow mark is not clear because the mechanism of flow mark is not figured out till now. Any injection molding analysis software can not predict the flow mark phenomena. To solve weldline and flow mark defects, the gate thickness is reduced to increase the melt front velocity and the melt front velocity of the flow mark area is increased from 82.3mm/s to 104.7mm/s. In addition, the bulk temperature of the flow mark area is increased from $178.3^{\circ}C$to $215.2^{\circ}C$ by adding a cold slug well. The flow mark phenomena can be greatly reduced by increasing the flow front velocity and elevating the bulk temperature.

• Journal of Mechanical Science and Technology
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• 제20권8호
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• pp.1256-1265
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• 2006

The supersonic flows around tandem cavities were investigated by two-dimensional and three-dimensional numerical simulations using the Reynolds-Averaged Navier-Stokes (RANS) equation with the k- ω turbulence model. The flow around a cavity is characterized as unsteady flow because of the formation and dissipation of vortices due to the interaction between the freestream shear layer and cavity internal flow, the generation of shock and expansion waves, and the acoustic effect transmitted from wake flow to upstream. The upwind TVD scheme based on the flux vector split with van Leer's limiter was used as the numerical method. Numerical calculations were performed by the parallel processing with time discretizations carried out by the 4th-order Runge- Kutta method. The aspect ratios of cavities are 3 for the first cavity and 1 for the second cavity. The ratio of cavity interval to depth is 1. The ratio of cavity width to depth is 1 in the case of three dimensional flow. The Mach number and the Reynolds number were 1.5 and $4.5{\times}10^5$, respectively. The characteristics of the dominant frequency between two- dimensional and three-dimensional flows were compared, and the characteristics of the second cavity flow due to the first cavity flow was analyzed. Both two dimensional and three dimensional flow oscillations were in the 'shear layer mode', which is based on the feedback mechanism of Rossiter's formula. However, three dimensional flow was much less turbulent than two dimensional flow, depending on whether it could inflow and outflow laterally. The dominant frequencies of the two dimensional flow and three dimensional flows coincided with Rossiter's 2nd mode frequency. The another dominant frequency of the three dimensional flow corresponded to Rossiter's 1st mode frequency.

• International Journal of Air-Conditioning and Refrigeration
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• 제15권3호
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• pp.114-121
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• 2007

In this study, a modified reverse flow type, one of the triple effect absorption cycles, is studied for performance improvement. The cycle simulation is carried out by using EES(Engineering Equation Solver) program for the working fluid of $H_2O/LiBr$ solution. The split-ratios of solution flow rate, UA of each component, pumping mass flow rate of solution are considered as key parameters. The results show that the optimal SRH (split ratio of high side) and SRL (split ratio of low side) values are 0.596 and 0.521, respectively. Under these conditions, the COP is maximized to 2.1. The optimal pumping mass flow rate is selected as 3 kg/s and the corresponding UAEV A is 121 kW/K in the present system. The present simulation results are compared to the other literature results from Kaita's (2002) and Cho's (1998) triple effect absorption systems. The present system has a lower solution temperature and a higher COP than the Kaita's modified reverse flow, and it also gives a higher COP than the Cho's parallel flow by adjusting split ratios.

• 한국가시화정보학회지
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• 제14권2호
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• pp.12-17
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• 2016

In this work, we investigate the flow velocity controllability of a diffuser-type multiple hydrofoil duct by experimental and numerical flow visualization approaches. The flow velocity controllability is analyzed by changing the angle of the hydrofoil near the outlet, which is the diffuser, while the incoming flow velocity is 0.6 m/s in the experiment. When the diffuser angle is changed from 0 to 7.5 degree, the maximum velocity inside the duct is varied from 1.35 m/s to 1.52 m/s. Also, it is shown from the numerical analysis that the maximum velocity is varied from 1.09 m/s to 1.17 m/s in the same condition. Thus, the aspect of the acceleration in the duct due to the increase of the diffuser angle is similar between the both approaches. Therefore, the multiple hydrofoil duct can be used to control the flow speed inside the duct for continuously extracting power close to a rated capacity.

• Tribology and Lubricants
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• 제17권3호
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• pp.236-243
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• 2001

In this study, flow factors are evaluated in terms of kurtosis using random rough surface generated numerically. As h/$\sigma$become large ø$\sub$x/, ø$\sub$y/, ø$\sub$fp/, approach to 1 and ø$\sub$s/, ø$\sub$fs/ to 0 asymptotically regardless of kurtosis. ø$\sub$x/, ø$\sub$y/, ø$\sub$fp/ increase with increasing kurtosis in the mixed lubrication regime. ø$\sub$s/, ø$\sub$fs/ is associated with an additional flow transport due to the combined effect of sliding and roughness. As h/$\sigma$ decreases ø$\sub$s/, ø$\sub$fs/ increase up to a certain point, and then decrease toward zero. This behavior can be attributed to the increasing number of contacts in the mixed lubrication regime. ø$\sub$x/ in the presence of elastic deformation on the surface is larger than ø$\sub$x/ in the absence of it because local film thickness(h$\sub$T/) increases by elastic deformation.

• 한국컴퓨터정보학회논문지
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• 제17권2호
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• pp.69-76
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• 2012

본 연구의 목적은 웹상에서 이루어지는 컴퓨터 교과목 이러닝에서, 학습자의 학습만족도와 자기주도성, 플로우(flow) 경험의 연관관계를 파악하고, 경로분석을 활용하여 이들 요인간의 인과관계를 분석, 규명하는 것이다. 이를 위해 기존 이론 연구들을 바탕으로 학습만족도를 종속변인으로 하고 자기주도성과 플로우 경험을 독립, 매개변인으로 하는 구조모형을 기초로 하여, 각 요인의 하위 구성요인 간의 인과관계를 분석하였다. 총 193명 학생의 데이터가 분석에 이용되었으며, 주요 결과를 요약하면 다음과 같다. : 1. 학습자의 자기주도성은 플로우 경험을 매개변인으로 하여 학습만족도에 간접적으로 유의한(p<.01) 영향을 미치는 것으로 나타났으며, 플로우 경험은 학습만족도에 직접적으로 유의한(p<.01) 영향을 미치는 것으로 나타났다; 2. 자기주도성의 7개 하위 구성요인 중 '독창적 접근', '학습에 대한 사랑', '학습자적 신념' 등이 플로우 경험을 매개로 하여 학습만족도에 양(+)의 방향으로 간접적으로 유의한(p<.01) 영향을 미치는 것으로 나타났으며, 플로우 경험의 9개 하위 구성요인 중 '명확한 목표' 요인이 학습만족도에 양의 방향으로 직접적으로 유의한(p<.01) 영향을 미치는 것으로 파악되었다.

• 한국유체기계학회 논문집
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• 제7권4호
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• pp.40-46
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• 2004

This paper is concerned with the numerical analyses of an S-shaped duct for the inter-channel between compressor spools. For the compactness and lightweight of an engine, the length of the S-shaped duct is desired to be minimized. Shortening the S-shaped duct, however, flow separation is likely to occur. Numerical investigation using a three-dimensional Navier-Stokes flow solver was performed to determine the availability of the minimization of an S-shaped duct. Computations were performed introducing the experimental data as the inlet flow condition of the OGV in determining the minimum length of the S-shaped duct. Also, the leaning effect of the OGV which assists the flow to turn radially inward was studied adopting mixing-plane method to consider the rotor/OGV interaction.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2002년도 추계 학술대회논문집
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• pp.121-126
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• 2002

Aircraft propulsion systems often use diffusing S-duct to convey air flow from the wing or fuselage intake to the engine compressor, Well designed S-duct should incur minimal total pressure losses and deliver nearly uniform flow with small transverse velocity components at the engine compressor entrance. Reduced total pressure recovery lowers propulsion efficiency and nonuniform flow conditions at the engine face lower engine stall limits. In this study, S-duct which has maximum total pressure recovery and nearly uniform flow profiles at the compressure intake should be found using design optimization methods with 3-dimensional Wavier-Stokes analyses.