• Proceedings of the Korea Water Resources Association Conference
• /
• 2019.05a
• /
• pp.238-238
• /
• 2019

산지계곡에는 큰 자갈이나 호박돌이 무더기로 퇴적되어 있어서 대규모 공극을 구성한다. 호우시 이 돌무더기 내부에 빠른 흐름이 형성되고 이에 따른 퇴적사면의 급격한 변동이 발생하기도 한다. 본 연구에서는 대공극 매질의 흐름은 산지계곡에 퇴적된 균일 직경을 가진 구형 입자로 구성된 대규모 공극 매질을 구성하고, 비 Darcy 흐름의 유속에 미치는 입경의 영향을 수리실험으로 조사하였다. 실험에 사용된 구형 입자는 크기가 15.5mm, 25mm, 36.5mm인 유리구슬이고, 조성된 매질의 공극율은 Table 1과 같으며, 실험에서 침투거리는 40cm로 하였다. 실험유량은 0.98~15.41 t/s이고 입자 Reynolds 수는 120~4,580의 범위였다. 동수경사가 증가하면 매질의 단면평균 유속이 비선형적으로 증가하였다. 입경이 작을수록 유속과 동수경사 사이의 비선형적 경향이 더 크다(Fig.1). 동일한 동수경사에서 매질의 입경이 클수록 유속이 빠르게 나타났다.

• Proceedings of the Korean Nuclear Society Conference
• /
• 1996.05d
• /
• pp.88-94
• /
• 1996

원자력발전소의 공조계통에 설치되어 운영되는 기체 방사성물질 제거용 첨착 활성탄 탑내에서 균일한 공기 유속분포가 유지되고 있는지를 확인하기 위한 실험을 실시하였다. 본 실험에 사용되는 장비(Tester for Flow Distribution, 이하 TFD라 함)는 원자력발전소에서 사용하는 첨착 활성탄 필터(Adsorber)내의 흡착층을 모방하여 자체에서 제작하였으며, 시험조건들은 실제의 값을 기준으로 적용하였다. 각 위치에서의 보정된 용적 유속을 구하기 위해 자체에서 만든 "FLOWD"라는 계산프로그램을 사용하였으며, 입구 및 출구측 공간에 10" 간격으로 각 6개씩 유속 감지기를 설치하여 면속도를 구하였다. 각 지점에서의 면속도는 평균 0.24449m/s로 각 구간에서의 겉보기 면속도의 분포는 매우 균일한 값을 나타내었으며, 약 2% 이내의 편차로 활성탄 탑내에서의 공기의 흐름이 균일하게 통과함을 확인할 수 있었다.통과함을 확인할 수 있었다.

• Proceedings of the Korean Nuclear Society Conference
• /
• 1999.05a
• /
• pp.166-166
• /
• 1999

• Proceedings of the Korean Nuclear Society Conference
• /
• 2002.05a
• /
• pp.116-116
• /
• 2002

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.31 no.4
• /
• pp.92-98
• /
• 2003

The optimum design of Hanyang low speed wind tunnel has been performed to augment flow uniformity and to reduce turbulence intensity of wind tunnel test section have to be known for reliability of wind tunnel test. The non-uniformity and turbulence intensity of Hanyang low speed wind tunnel were measured with Pilot tube and X-type hot-wire probe at various wind speeds. As the results, the non-uniformity decreases as the wind speed increases. The non-uniformity is relatively high in the proximity of the diffuser. The turbulence intensity is a little higher than design requirement in the middle of the test section.

• Bulletin of the Society of Naval Architects of Korea
• /
• v.26 no.3
• /
• pp.1-8
• /
• 1989

The flow characteristics of a circulating water channel which is appropriate for a flow measurement and visualization in the laboratory has been investigated by using a Laser Doppler Anemometer. In order to get a stable and uniform distribution of mean velocity at the test section, the surface flow accelerator is designed and used. The experimental results that the turbulent structure should be considered with the mean velocity for obtaining the reasonable uniformity at the test section.

• Clean Technology
• /
• v.13 no.3
• /
• pp.195-200
• /
• 2007

This study investigated the flow rate changes of the heterogeneous rectangular microchannels which have different hydrophilic property on the bottom surface. The heterogeneous rectangular microchannel has three native PDMS (poly-dimethyl siloxane) surfaces which were patterned by the soft lithography. PDMS bottom surface was treated by the argon plasma and coated by the allyl alcohol (99%). The channel length was 10, 20 and 30 mm and the channel width was 100, 200 and $300\;{\mu}m$, respectively. Several external voltages were applied to make the fluid flow by the electroosmosis in the microchannel. For the same electric field strength and hydrophilicity of the bottom surface, the flow rate is almost same. This result is matched to the theoretical expectation and confirms that the experimental system is reliable. With increasing the channel width, the flow rate increased for the same hydrophilicity of the bottom surface. The flow rate of the microchannel of higher hydrophilicity was larger than that of the microchannel of lower hydrophilicity. This result implies that the hydrophilicity change of the bottom surface could be applied to control the flow rate in the microchannel.

• Journal of the Korea Academia-Industrial cooperation Society
• /
• v.14 no.2
• /
• pp.962-969
• /
• 2013

This study used Computational Fluid Dynamics(CFD) to assess the properties of the air current inflow and the flow velocity distribution in the fume hood. In order to verify the effect of improvement, it was also predicted the characteristics of the flow pattern in case the hood face is structurally improved. The assessment of the capture velocity with the existing fume hood confirmed maximum 23 to 30% difference as compared to the root mean square (RMS). And the hood face showed great difference in flow velocity, with the flow velocity in the upper part is 58 to 68% faster than that in the lower part of the hood. So, as a result of the improvement of the hood designed to maintain a steady exhaust at the hood face (that is, installing a baffle on the inner wall and designing the slot type face), a difference of maximum 7% as compared to RMS appeared while maximum 12% differentiation in flow velocity through sections was predicted, showing mitigation of much of the difference in control velocity as compared to the previous structure.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2006.05a
• /
• pp.130-134
• /
• 2006

The injection uniformity of the fuel manifold in a liquid rocket engine has been analyzed with dividing plates to improve the cooling performance at the face plate. Three dimensional computational fluid dynamics analysis has been performed to compare the injection uniformity for 5 candidate designs and has been verified to compare with the measured data for the optimal manifold design. For the case I and II, the coolant mass flux increases as the whole working fluid is enforced to flow under the dividing plate. The injection uniformity decreases due to the variation of mass flux at the end of dividing plate and the concentration of mass flow rate at the center of manifold. However case III and IV have uniform injection performance due to reduced mass flux concentration as the coolant can flow along both upper passage and lower passage of the dividing plate. Among the candidate designs, case IV is thought to be the optimal dividing plate with regard to cooling performance and injection uniformity.

• Proceedings of the Korean Vacuum Society Conference
• /
• 2012.02a
• /
• pp.116-116
• /
• 2012

위성의 발사, 천이궤도, 운영궤도 등에서 위성체에 주어지는 극한 온도와 진공상태에서 위성체와 열제어시스템이 요구 조건을 만족시키는가를 확인하기 위하여 열진공시험을 수행한다. 우주에서 일어나는 환경변화는 극도로 심해서 지상에서 이와 유사한 열적 환경을 모사하는 방법은 쉽지가 않고, 일반적으로 위성체에 대한 열진공/평형 시험을 위해서는 열유속 흡수법과 열유속 투사법의 두 가지 방법을 사용한다. 한국항공우주연구원에서는 종래 접촉식 히터를 위성체에 직접 부착하는 방법에서 탈피하여 새로이 IR Lamp를 이용한 열유속 흡수법을 이용하여 위성체에 계산된 열유속을 인가하는 방법으로 위성체 열진공/평형시험을 수행하였으며, IR Lamp는 요구되는 100W~400W 사이의 열량을 오차 범위 5% 이내로 인가하여 균일한 온도 분포를 유지하고 성공적인 시험을 수행하였다.