• 한국수자원학회논문집
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• 제56권spc1호
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• pp.1049-1058
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• 2023

보와 저낙차 댐과 같은 하천횡단구조물을 통과하는 흐름은 도수 현상을 동반하는 급변류가 지배적이다. 구조물 하류에서 도수로 인한 유속과 수면의 강한 비정상성은 수공구조물의 안정에 영향을 줄 수 있다. 특히, 높은 Froude 수 조건에서 발생하는 정상도수는 공기연행이 현저하게 발생하여 흐름 특성은 더욱 복잡해진다. 이 연구에서는 Froude 7.3 조건에서 발생하는 정상도수를 모의하기 위해서 큰와모의 기법과 하이브리드 VoF 기법을 이용한 수치모의를 수행하였다. 수치모의 결과는 구조물 하류 바닥면에서 계측된 순간최대압력과 시간평균압력 분포를 유사하게 재현하는 것으로 나타났다. 단, 구조물 직하류에서의 순간최소압력 분포는 대상으로 하는 실험 계측값과 반대의 양상을 보이지만, 유사한 다른 시험과는 같은 양상을 보임으로써 본 연구에서 수행한 수치모의는 합리적으로 압력변동을 예측하는 것으로 판단된다. 도수 중앙부에서의 연직방향 유속분포와 공기농도분포는 유사한 조건의 실험 결과들과 자기상사성을 보이면서 양호하게 일치하는 것으로 나타났다. 이러한 결과는 본 연구에서 적용한 큰와모의 기법과 하이브리드 VoF 기법이 높은 Froude 수 조건에서 강한 공기연행을 동반하는 도수현상을 양호하게 재현할 수 있음을 보여준다.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2006년 제4회 한국유체공학학술대회 논문집
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• pp.327-330
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• 2006

This paper represents the numerical analysis on effects of radius ratio in a concentric annulus with a rotating inner cylinder. The numerical model consisted of two cylinder which inner cylinder is rotating and outer cylinder is fix, and the axial direction is used the cyclic condition because of the length for axial direction is assumed infinite. The diameter of inner cylinder is assumed 86.8mm, the numerical parameters are angular velocity and radius ratio. Also, the whole walls of numerical model have no-slip and the working fluid is used water at $20^{\circ}C$. The numerical analysis is assumed the transient state to observe the flow variations by time and the 3-D cylindrical coordinate system. The calculation grid adopted a non-constant grid for dense arrangement near the wall side of cylinder, the standard $k-{\omega}$ high Reynolds number model to consider the effect of turbulence flow and wall, the fully implicit method for time term and the quick scheme for momentum equation. The numerical method is compared with the experimental results by Wereley and Lueptow, and the results are very good agreement. As the results, TVF isn't appeared when Re is small because of the initial flow instability is disappear by effect of the centrifugal force and viscosity. The vortex size is from 0.8 to 1.1 for TVF at various $\eta$, and the traveling distance for wavy vortex have the critical traveling distance for each case.

• 한국미생물·생명공학회지
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• 제20권4호
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• pp.445-450
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• 1992

동물세포 배양기에서 silicone tube를 oxygenator로 이용하여 산소전달 정도를 조사하였다. Silicone tube를 이용할 때 표면통기에 비해 산소전달 상수 $k_{\iota}a$는 약 30배 이상 증가하였다. 통기속도와 교반소도가 증가할 수록 $k_{\iota}a$값도 증가하지만 교반속도가 훨씬 효과적이었고, 물질전달에 관한 무차원 상수 tubing Sherwood number(Sh)와 유체 흐름에 관한상수 impeller Reynolds number(Re)는 log-log 좌표에서 직선관계가 있었고 기울기는 tube 길이에 관계없이 0.26이었다. Tube 길이는 2m가 적당하였고 impeller는 pitched blade type이 효과적이었다.5%serum이 첨가된 medium에서는 $k_{\iota}a$가 40%로 감소하여Tekl. HepG2를 이용한 실제 동물세포 배양에서는 전형적인 세포농도인 4~$6{\times}10^6$ cells/m$\ell$ce를 얻을 수 있었다.

• 한국추진공학회지
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• 제17권3호
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• pp.37-46
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• 2013

최근, micro shock tube는 Micro combustion, Micro propulsion, Particle delivery systems 등과 같은 다양한 공학응용분야에서 사용 되고 있다. Micro shock tube 에서 일어나는 유동 특성은 아주 작은 레이놀즈수 와 높은 누센수의 영향으로 인해 잘 알려진 기존의 macro shock tube 유동 특성과 상당한 차이가 나타난다. 또한 기존의 많은 shock tube의 순간적 과정으로 간주되는 격막파막 과정은 micro shock tube의 격막 근처의 유동장과 충격파 형성을 결정하는 중요한 요인이 될 것이다. 본 논문에서는 micro shock tube를 모사하기 위해 축 대칭, Maxwell's 슬립속도 조건과 온도 변화 경계 조건을 적용하여 수치 해석을 수행 하였다. 또한 유동장과 충격파 형성에 대한 유한 파막 과정의 영향을 자세히 조사 하였고, 결과로부터 충격파 강도는 micro shock tube를 통해 전파됨에 따라 급격히 감소하였다.

• 대한설비공학회:학술대회논문집
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• 대한설비공학회 2008년도 동계학술발표대회 논문집
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• pp.618-623
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• 2008

To enhancement heat transfer performance, the metallic foam as heat exchanger was studied rapidly. This was attributed to its high surface area to volume ratio as well as intensive flow mixing by tortuous flow passages. So the experimental study about the heat transfer characteristic of metallic foam is presented in this paper. The material in this experiment was used as FeCrAl which has density of 10 ppi, 20 ppi and 30 ppi respectively. And the results show the heat transfer is rise with permeability Reynolds number increase and the pressure drop metallic foam was increased with the ppi increase.

• 설비공학논문집
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• 제12권1호
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• pp.59-66
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• 2000

In a previous paper, we have examined the effects of nozzle configuration and jet to jet spacing on the heat transfer of 1 row of circular water jets. In this paper, experiments have been conducted to obtain the effects of nozzle to target plate distances on the heat transfer of 1 row of 3 jets and 1 row of 5 jets. The nozzle configurations are Cone type, Reverse cone type and Vertical circular type. Nozzle to target plate distance H was varied from 16 mm(H/D=2) to 80mm(H/D=10). For fixed value of mass flow rate and nozzle to target plate distance, larger values of average Nusselt number were obtained for the smaller jet to jet spacing. For the array of water jets, the average heat transfer was decreased slightly with increasing nozzle to target plate distance at low jet velocity of $\textrm{V}_{o}$=3 m/s. However, except for $\textrm{V}_{o}$=8 m/s of 1 row of 5 jets, it was increased with increasing nozzle to target plate distance at high jet velocity of $\textrm{V}_{o}$$\geq$6m/s. We proposed to apply the nozzle configuration of maximum average heat transfer to each nozzle to target plate distance for 1 row of 3 jets, and, it was Reverse cone type nozzle for 1 row of 5 jets(Reynolds number$\geq$36000).

• 한국항공우주학회지
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• 제32권8호
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• pp.72-81
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• 2004

초고속 지상 운행체에 대한 풍동실험을 통하여 단단한 채널과 운행체 사이에 발생하는 공력 상호작용을 연구하였다. 풍동실험시 유속은 30m/see에서, 단위길이당 레이놀즈수는 $3.1{\times}10^5/m$였다. 가변지면과 안내로와 같은 실험장치들이 이 실험을 위해 사용되었다. 운행체는 지면과 운행체 사이의 거리가 가까워질수록, 안내로 사이의 간격이 좁아질수록 양력은 급격히 증가하였고, 항력은 미세하게 감소하였으며, 키놀이 모멘트는 억제되어 정안 정성을 증대시켰다. 연선을 사용한 유동가시화를 통하여 운행체가 채널 내를 운행할 때의 유동 특성을 채널이 없는 경우와 비교하였고 공력측정 결과를 뒷받침하였다. 채널 지연과 안내로의 영향으로, 운행체 하부에서의 유동은 날개의 익단판 외부로 흐르지 못하며, 이것이 운행체 양력증가의 주요 원인이 되었다.

• 대한조선학회논문집
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• 제54권6호
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• pp.515-521
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• 2017

Large Cavitation Tunnel (LCT) of KRISO enables us to conduct cavitation tests of the propeller attached to a ship model. As the ship model tests are done at rather high Reynolds number of 107~108, flow measurement system such as pitot tube cannot be employed because of structural safety problems in its system and difficulties in installing it within the test section. Thus, KRISO has developed new 3-D LDV system used in large test section of LCT. There are several difficulties in using 3-D LDV, which did not allow efficient operation of it. The first trouble was the calibration using the conventional pin hole. To make the focus with same laser-beam waists at the wanted position, the high spatial resolution CCD is utilized in the calibration procedure for 3-D LDV. The off-axis configuration provides two velocity components in the horizontal plane and on-axis configuration gives third velocity component in the vertical plane. The horizontal velocity components are also obtained in the coincidence mode, which prevents any misleading results in the off-axis configuration. The nominal wake of Aframax tanker model is measured by the developed 3-D LDV system. The measured hull wake showed good agreement with that obtained by CFD calculation.

• 한국가시화정보학회:학술대회논문집
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• 한국가시화정보학회 2007년도 추계학술대회
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• pp.134-137
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• 2007

The temporal evolution of wake behind a circular cylinder oscillating rotationally with a relatively high forcing frequency has been investigated experimentally using a dynamic PIV technique. Experiments were carried out with varying the frequency ratio $F_R\;(=f_f/f_n)$ in the range from 0.0 (stationary) to 1.6 at oscillation amplitude of ${\theta}_A=30^{\circ}$ and Reynolds number of $Re=4.14{\times}10^3$. Depending on the forcing condition ($F_R$), the flow was divided into three regimes; non-lock-on ($F_R=0.4$), transition ($F_R=0.8$, 1.6) and lock-on regimes ($F_R=1.0$) with markedly different flow structure in the near-wake region behind the cylinder. When the frequency ratio was less than 1.0 ($F_R{\le}1.0$), the rotational oscillatory motion of the cylinder decreased the length of the vortex formation region and enhanced the mutual interaction between large-scale vortices across the wake centerline. The entrainment of ambient fluid seemed to play an important role in controlling the near-wake flow and shear-layer instability. However, the flow characteristics changed markedly beyond the lock-on flow regime ($F_R=1.0$) due to high-frequency forcing. At $F_R=1.6$, the mutual interactions between the vortices shed from both sides of the cylinder were not so strong. Thereby, the flow entrainment and momentum transfer into the wake center region were reduced. In addition, the size of the large-scale vortices decreased since the lateral extent of the wake was suppressed.

• 대한기계학회논문집B
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• 제32권4호
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• pp.283-289
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• 2008

An experimental investigation was conducted to investigate the heat/mass transfer for impingement/effusion cooling system with inclined jet. Jets with inclined angle of 60 are applied to impingement/effusion cooling. At the jet Reynolds number of 10,000, the experiments were carried out for blowing ratios ranging from 0.0 to 1.5. The local heat/mass transfer coefficients on the effusion plate are measured using a naphthalene sublimation method. The result indicates that the inclined jet causes the non-uniform and low heat/mass transfer compared to the vertical jet. At stagnation region, the peak position is shifted from the geometrical center of injection hole due to Coanda effect and its level is higher than that of vertical jet due to increase in turbulence intensity by steep velocity gradient near the stagnation region. Further, the secondary peak region disappears because the interaction between adjacent wall jets weakens. When the initial crossflow occurs, the distorted heat/mass transfer pattern appears. As the blowing ratio (crossflow rate) increases, the heat/mass transfer distributions become similar to those of the vertical jet. This is because the effect of crossflow is dominant compared to that of inclined jet under high blowing ratio $(M{\geq}1.0)$. At low blowing ratio $(M{\leq}0.5)$, averaged Sh value is 10% lower than that of vertical jet, whereas its value at high blowing ratio $(M{\geq}1.0)$ is similar to that of vertical jet.