• Journal of the Korean Society of Marine Environment & Safety
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• v.20 no.5
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• pp.552-557
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• 2014

The objective of the This study is to access the speed performance employing the sea trial test and CFD with the our own designed and manufactured one-man boat. The overall design process including hull form design was explained. The sea trial was carried out with a manufactured boat in the clam sea. Brake power at the design speed of a boat through the sea trial was measured as 1680 W. The flow computation was conducted considering free surface and dynamic trim using a commercial CFD code(STAR-CCM+). The result of computation provided the information that residual resistance is bigger than fraction's at design speed. The total efficiency were predicted based on the sea trial and CFD. The Total efficiency was divided into shaft efficiency and quasi-propulsive efficiency. By using quasi-propulsive efficiency, it becomes possible to predict speed performance of boat in future. The results can provide information regarding hull form design, performance analysis and development of a boat in future.

• Proceedings of the Korea Water Resources Association Conference
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• 2012.05a
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• pp.558-558
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• 2012

다수의 자연 하천은 유사 이동과 하안의 침식으로 인하여 사행 하천이 발생한다. 사행 하천에서의 이차류는 원심력, 편수위로 발생하는 중력에 의한 압력차, 그리고 난류로 인하여 발생하는 응력으로 인하여 형성되며 나선형 구조 형태로 표면 유속은 외부로 향하고 하천 바닥의 유속은 안으로 향하게 된다. 이러한 2차류의 형성은 주 흐름의 특성을 변형시킨다. 자연하천에서 2차류는 주 흐름의 15-25%의 크기를 가지고 있으나, 하상의 변화, 유사의 이동 등과 연관되므로 2차류의 영향을 정확히 해석하는 것은 수리학적으로 매우 중요하다. 본 연구에서는 사행수로에서 발생하는 2차류 거동을 수치모의를 통하여 수행하였다. 우선 2차류의 분석을 위하여 실험을 통한 결과물을 비교하였다. 자연 하천의 특성을 반영할 수 있도록 서일원(2006)이 수행한 S-자 형태의 실험 수로의 실험 결과를 분석하였다. 수치 모의를 위하여 3차원 전산유체역학 프로그램을 사용하여 사행수로의 2차원 유속 구조를 모의할 수 있도록 하였다. FLOW-3D 프로그램을 이용하여 실험 결과와 모의 결과를 비교할 수 있도록 하였으며 비교 후 보정을 실시하였다. 모의는 주로 LES (Large Eddy Simulation) 모형을 통해 이루어졌으며, 이를 통하여 실험에서 획득한 결과와 비슷한 유속구조 분포를 확인할 수 있었다. 보정 및 검증 후 수치 모의를 통한 유속 데이터를 이용하여 민감도 분석을 실행하였다. 이후로는 수로의 만곡부, 조도, 수심 등 인공수로의 조건을 변경하여 수치 모의를 수행하였다. 보정된 결과를 이용하여 추가적인 모의를 통한 유속 분포 구조의 비교가 이루어졌다. 이를 통하여 각 조건이 이차류의 크기에 미치는 영향을 확인할 수 있었으며, 모의를 통한 유속분포 결과는 대체적으로 실험을 통한 이차류의 연직분포 구조와 일치하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.4
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• pp.245-255
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• 2019

This paper describes on aerodynamic analysis based on the truncation rate of guided-weapon nose using computational fluid dynamics. The shape to perform the analysis is only the body of the guided weapon and the diameter to length ratio is 10.7. Three nose shapes were selected and hemisphere, 25% and 50% truncation were compared. For the accurate CFD analysis of the body, the grid method and the analytical method were selected and verified using NASA wind tunnel test data. For the three nose shapes, the drag analysis for the flight Mach number is 6~20% different. This difference was analyzed by the pressure distribution from nose to base.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.37 no.10
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• pp.927-932
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• 2013

The intracranial aneurysm model is extracted based on the Computed Tomography (CT) scan images. Computational fluid dynamics simulations were conducted under both steady and realistic flow conditions in ANSYS-FLUENT. The minimum wall shear stress in the intracranial aneurysm tended to occur in the aneurysmal region. The magnitude of wall shear stress along inner wall of the curvature in the right M1 segment of middle cerebral artery is approximately 20 times higher than that along both the proximal and distal walls. However, the magnitudes of the wall shear stress at the aneurysm region were considerably low. The blood flow has the complex distribution in the aneurysmal region during the systolic period. Complex helical flow patterns are observed inside the aneurysm. Through an analysis of the hemodynamic characteristics, one may predict the rupture of the cerebral aneurysms.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.36 no.7
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• pp.767-774
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• 2012

A fluidic device (FD) has been adopted in the safety injection tanks (SITs) of APR1400. A flow control mechanism of the FD was used to vary the flow regime in the vortex chamber corresponding to the SITs water level. The flow regime in the vortex chamber has a different pressure loss from low to high in accordance with the SITs water level. Nitrogen at the top of the SIT could be released owing to inertia of discharge flow when changing from a high flow rate to a low flow rate. This phenomenon is important to design improvement perspective because it can affect the performance of the FD. This paper shows a result of a preliminary numerical study to obtain the transient data related to air release in the flow turn-down period using a two-fluid free-surface model provided from ANSYS CFX 13.0. In conclusion, there is no significant effect on the performance of the FD, though a small quantity of air is released during the flow turn-down period.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.4
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• pp.253-260
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• 2013

Ice accretions on the surface around a rotorcraft air intake can deteriorate the safety of rotorcraft due to the engine performance degradation. The computational simulation based on modern CFD methods can be considered extremely valuable in analyzing icing effects before exact but very expensive icing wind tunnel or in-flight tests are conducted. In this study the range and amount of ice on the surface of anti-icing equipment are investigated for heat-on and heat-off modes. It is demonstrated through the computational prediction and the icing wind tunnel test that the maximum mass and height of ice of heat-on mode are reduced about 80% in comparison with those of heat-off mode.

• Journal of the Korean Applied Science and Technology
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• v.36 no.4
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• pp.1080-1087
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• 2019

For a risk analysis in a chemical process, it is important to reflect correctly the characteristic properties of the target process. In this study, computational fluid dynamics (CFD) was adopted for the advanced risk analysis in a residual hydro desulfurization (RHDS) process by considering operation condition, layout of instruments and facilities, atmospheric condition, and wind direction. Release and explosion simulations for the RHDS by using FEA (Finite Element Analysis) and CFD showed the applicability of 3D scanning methods for estimation of release hole size and release amount.

• Proceedings of the Korea Society for Energy Engineering kosee Conference
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• 2006.05a
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• pp.164-169
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• 2006

본 연구는 가정용 가스 보일러의 배기가스 유동특성을 전산유체역학을 이용하여 정밀 분석하고 CO 검지 장치의 최적화 설계를 결정하는 것을 목적으로, CFD 상용코드 FLUENT 6.2를 이용하였다. 배기가스 포집위치에서 가스 유속의 균일성과 CO농도 검출기에서의 속도가 주요 성능 인자이며 포집기의 위치, 포집구멍의 크기 및 배기가스의 유량을 주요 변수로 선택하였다. 포집기의 위치는 배기부의 상부와 하부인 두가지의 경우이고 두 경우의 배관 높이 차이는 10 mm이다. 포집구멍의 직경 변화는 3 mm, 4 mm 및 5 mm인 세가지 경우이다. 마지막 변수인 배기가스의 유입속도는 20,000 kcal/hr용량의 k사 가스 보일러가 공기비 1.1일 경우에 정상 연소시 0.5 m/s임을 알았고 저부하와 고부하일 경우를 고려해서 0.3 m/s, 0.5 m/s 및 0.7 m/s의 세가지 경우를 변수로 결정하여 총 18가지 형태의 대상을 전산유체 역학을 통해서 분석하였다. 궁극적인 목표였던 배기가스의 균일성은 한가지 경우를 제외 하고는 만족할만한 결과를 얻었기 때문에 CO검지 장치가 위치할 곳에서의 속도 및 포집구멍의 크기가 CO농도 검출기 유속의 주요 인자라 할 수 있다. 결론적으로 포집구멍의 크기가 5 mm인 6가지 경우 중에서 두가지 경우는 검지장치의 유효속도를 초과하였고 포집구멍의 크기가 3 mm인 경우는 검지장치의 유입 속도가 상대적으로 작으므로 포집구멍의 크기는 4 mm가 적합한 것으로 판단하였다.

• Journal of Korean Society of Coastal and Ocean Engineers
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• v.19 no.5
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• pp.476-483
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• 2007

One of the main function of Ieodo Ocean Research Station is to service the information about the weather and fishing grounds condition which are collected through calibrating convection flow and ocean current around the station. However, due to the influence of the station's structure below sea level, it is difficult to obtain the exact flow data. Therefore, it is required to research on the effect of the structure and the method to evaluate and revise the observed data. In this paper, as a basic study, it deals with the algorithm that simulate the interaction between ocean current and the station structure, followed by discussions about the way to applicate the algorithm. Through 3-dimensional computational fluid dynamics analyses (using Navier-Stokes equations with K-turbulence model), the influence of the station and submerged rocks are quantitatively evaluated, and we would suggest methods how to obtain accurate flow information from the measured rough data.

• Aerospace Engineering and Technology
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• v.6 no.1
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• pp.14-18
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• 2007

The ground effect on tilt-rotor UAV is analyzed by simulating the hovering UAV for various altitudes. Ground effect increases pressure beneath the UAV body and generates additional lifting force. The ground effect diminishes at altitude 3m and hovering UAV generates constant lifting force above 3m.