• Proceedings of the Acoustical Society of Korea Conference
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• 1992.06a
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• pp.91-95
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• 1992

개영역(open boundary) 내의 변환기에 대한 음장 특성은 경계 조건이 좌표계와 정합되는 특수한 경우 헤름홀쯔 방정식풀이로 그렇지 않은 복잡한 형태의 음장에 대해서는 경계적분법이나 근사해법으로 얻어진다. 그러나 최근 이러한 문제들은 발달된 컴퓨터의 계산능력으로 유한요소법이나 경계요소법을 이용한 수치해법으로 해결되고 있다. 본 연구에서는 경계조건 변화에 따른 원통형 압전변환기의 방사임피던스 및 지향특성을 유한요소법 및 하이브리드형 무한요소법을 이용하여 구하고 기존의 해석적 결과와 비교하여 수중용 변환기 제작의 설계에 대한 기초자료를 제공하고자 한다.

• Journal of Korean Society of Coastal and Ocean Engineers
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• v.27 no.6
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• pp.391-405
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• 2015

A global tsunami prediction system was suggested for a distant tsunami using a finite fault model and a cyclic boundary condition. The possibility of the suggested system as a distant tsunami response system was checked by applying it into the case of 2014 Chile tsunami. A comparison between the numerical results(tsunami height and arrival time) with different conditions (boundary condition, governing equation, grid size and fault model) and measured data (DART buoy, tide station) showed the importance of the finite fault model and the cyclic boundary condition.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.47-52
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• 2004

In the design of scramjet intake for hypersonic flight, a variety of aerothermodynamics phenomena are encountered. These phenomena include blunt leading - edge effects, boundary layer development issues, transition, inviscid / viscous coupling, shock - shock interactions, shock / boundary - layer interactions, and flow profile effects. For intakes that are designed to operate within a narrow Mach number / altitude envelope, an understanding of a few of these phenomena might be required. In this work several predominant flowfield phenomena (viscous phenomena, boundary - layer separation, and combustor entrance profile) are discussed to investigate the performance of the intake at the altitude and angle of attack extremes of the HyShot flight experiment.

• The Journal of the Korea Contents Association
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• v.8 no.4
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• pp.17-29
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• 2008

In Computer Graphics, fluid dynamics is used for animating and expressing the various special effects of water. As the hardware performance is getting higher, the several algorithms for fluid dynamics become to be executed in real time. However, it still requires a lot of computational time to get the realistic and detailed results. Therefore, there are many researches on the techniques of balancing between performance and quality. It must give priority to the executive performance preserving the visual reality even though sacrificing the physical reality, specially in applications with the game context which need to express the interaction between 3D objects and the surface of the water such as the sea or a lake. In this paper, we propose a method for the realtime animation of interactions between 3D objects and the surface of the water using the linear convolution of height fields and the bounding spheres of object.

• Journal of Korean Tunnelling and Underground Space Association
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• v.21 no.6
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• pp.861-874
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• 2019

A great interest in the seismic performance evaluation of small size tunnel structures such as utility tunnel has been taken since recent earthquakes at Pohang and Gyeongju in Korea. In this study, the three-dimensional dynamic analyses of vertical shaft and horizontal tunnel under seismic load were carried out using FLAC3D. Especially, parametric analyses was performed to investigate the effects of interfacial stiffness on interfacial behavior between soil and structure. The parametric analysis showed that the interfacial stiffness scarcely gave an effect on the global dynamic behavior of the structure, while had a significant effect on the local displacement behavior of the connections. The magnitude of the interfacial stiffness was inversely proportional to the displacement, while the magnitude of interface stiffness was proportional to the normal and shear stresses. The results of this study suggest the limitations of the existing empirical equations for interfacial stiffness and emphasize the need to develop new interfacial stiffness models.

• Transactions of the Korean Society of Mechanical Engineers
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• v.2 no.2
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• pp.38-41
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• 1978

이 논문에서는 표면의 일부에 기지의 압력을 밥는 긴 원주내의 응력분포를 구하는 문제를 고찰하였다. 문제를 혼합경계치조건에서 발생되는 쌍적분방정식의 해를 구하는 문제로 간단히 한후에 제 2종 Fredholm 적분방정식을 해결하는 문제로 하였다. 이 적분방정식의 수직해를 전자계산기에 의하여 구한 다음 도시하였다.

• Journal of the KSME
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• v.31 no.4
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• pp.332-340
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• 1991

본 글에서는 속이 찬 실린더(solid cylinder)에서의 비대칭 탄성파전파 문제를 풀기 위한 해석적 방법의 일부를 소개하고자 한다. 속이찬 실린더에 있어서는 측면벽의 경계조건에 상관없이 평 판에서의 Fourier 시리즈와 유사한 단순해가 존재하지 않는다고 밝혀져 왔다(1). 그러나 최근 발표된 본인의 논문(2)에서 지적된 것처럼, 매우 특별한 측면 경계조건을 갖는 경우에만 정해가 존재한다. 특히 탄성파전파에 관한 한, 이러한 정해는 물리적으로 볼 때 팽창파(dilatational wave)와 전단파(shear wave)가 서로 얽히지 않는 상태에 해당되기 때문에, 소위 "비혼합 해(uncoupled solution)"라 불린다. 이 "비혼합해(uncoupled solution)"의 실제 사용 예를 들면, 상술된 바와 같이 일반적인 측면 경계조건을 갖는 속이 찬 실린더 문제를 풀기 위한 시도함 수(trial function)로 사용될 수 있을 것이다. 주지하는 바와 같이 자유측면벽(traction-free cylindrical wall)을 갖는 속이 찬 실린더는 공학적으로 매우 중요한 구조요소이다. 이 경우에는 측면벽의 경계조건으로 말미암아, 해가 정해의 형태로 존재하지 않는다. 특히 이 구조물에서의 탄성파전파 문제를 다루고자 할 때, 먼저 분산관계식(dispersion relation)을 구한 다음, 이를 이 용해 경계문제를 푸는 것이 상용적으로 사용되는 방법이다. 이 분산 관계식은 파장과 주파수 와의 관계를 나타내는 것으로, 그 복잡성으로 말미암아 이 식을 사용되는 수치해법으로 정확하게 구하는 것은 거의 불가능하다. 따라서, 본 글에서는 특별한 측면벽을 갖는 속이 찬 실린더의 비혼합해를 활용하여 자유측면벽을 갖는 속이 찬 실린더의 분산관계식(pochhammer의 분산관 계식이라 불린다)을 구하는 법을 설명하고자 한다. 이를 위해 비혼합해가 존재하는 측면경계조 건에 대해 먼저 살펴보고자 한다.조 건에 대해 먼저 살펴보고자 한다.

• The Magazine of the Society of Air-Conditioning and Refrigerating Engineers of Korea
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• v.17 no.4
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• pp.418-425
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• 1988

Since conventional computer program is workable only with velocity boundary condition, in practical fluid passage such as clean room which usually have wide inlets and outlets, it is not easy to measure velocity itself because of its vector property. Furthermore a certain assumption of velocity at boundaries may lead to physically unreasonable results. From this motivation, we have developed a computer program to predict whole flow field imposed on pressure-based boundary condition which can be measured by relatively simple method. The only additional velocity boundary condition that should be imposed on to make the problem unique, are no slip condition at all walls and zero cross stream velocity at inlet. The result of present study was compared with that by Bernoulli equation being used practically. They were coincident well each other within 5%, therefore the validity of the present method is proved. In the present work, the flow field in a clean room subject to pressure-based boundary conditions at an inlet and two exits was predicted numerically. The pressure difference between the inlet and the left exit which keeps relatively low pressure among two exits is fixed as 150[Pa] and the pressure at the right exit is varied from zero to 150[Pa] by the increment of 25[Pa]. For each cases the flow characteristics in the clean room, the velocity profile at the inlet, and the flow rate through the two exits was predicted. The flow rate through the right exit imposed on relatively higher pressure than the left exit decreased linearly according to the increase of pressure of the right exit. When the pressure of the right exit is increased enough to cause back flow at the exit, the flow rate is rapidly decreased.

• Korean Architects
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• no.12 s.392
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• pp.56-59
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• 2001

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.12
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• pp.1025-1031
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• 2012

The present paper deals with concept design of supersonic inlet based on compressible flow theory and flow control of bleeding in order to guarantee stability of supersonic inlet of ramjet engine in broad range of operating conditions. Shock instability, shock wave-boundary layer interaction and flow separation should be properly controlled to improve performance of the supersonic inlet. Considering shock strength, boundary layer and flow separation, the supersonic inlet is modified from the basic model which is designed under inviscid theory. Consequently, shock is stabilized, and required mass flow rate is obtained. Furthermore, bleeding is applied to the supersonic inlet to maintain performance in off-design conditions. Mass flow condition is adopted for modeling of bleeding effect, and performance of the supersonic inlet is evaluated by changing bleeding locations and numbers.