• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2002년도 춘계학술대회논문집
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• pp.996-1000
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• 2002

A porous tube, comprised of a resin-coated woven fabric has recently been used as an effective component for use in intake systems of internal combustion engines to reduce the intake roaring. For the prediction of the acoustic performance of an engine intake system with a porous woven hose, the acoustic wall impedance of the hose must be known. Because of its peculiar acoustical and structural characteristics, the accurate measurement of the wall impedance ofa porous woven hose is not easy. A new measurement technique is proposed herein, that is valid over the low to mid frequency ranges. The acoustics impedance is inversely estimated from an overdetermined set of measured pressure transmission coefficients for specimens of different lengths and the reflection coefficient of end termination. The method involves only one measurement, and, as a result, it is very simple. The measured TL for samples with arbitrary conditions, arbitrary porous frequency, arbitrary length, and arbitrary mean flow condition, are in reasonably good agreement with values predicted from curve-fitted impedance data.

• 대한기계학회논문집
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• 제13권3호
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• pp.547-553
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• 1989

본 연구에서는 작동유체로서 수증기와 거동이 유사한 습공기를 대기 흡입식 풍동을 사용하여 원호 노즐로서 팽창시키는 경우에 대하여 응축충격파가 발생하는 흐름이 측정부내에 쐐기를 설치하여 발생시킨 경사충격파에 미치는 영향에 대해 실험적으로 조사하였다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2003년도 제20회 춘계학술대회 논문집
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• pp.91-93
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• 2003

A comprehensive numerical study is carried out to investigate for the understanding of the flow evolution and flame development in a supersonic combustor with normal injection of ncumally injecting hydrogen in airsupersonic flows. The formulation treats the complete conservation equations of mass, momentum, energy, and species concentration for a multi-component chemically reacting system. For the numerical simulation of supersonic combustion, multi-species Navier-Stokes equations and detailed chemistry of H2-Air is considered. It also accommodates a finite-rate chemical kinetics mechanism of hydrogen-air combustion GRI-Mech. 2.11[1], which consists of nine species and twenty-five reaction steps. Turbulence closure is achieved by means of a k-two-equation model (2). The governing equations are spatially discretized using a finite-volume approach, and temporally integrated by means of a second-order accurate implicit scheme (3-5).The supersonic combustor consists of a flat channel of 10 cm height and a fuel-injection slit of 0.1 cm width located at 10 cm downstream of the inlet. A cavity of 5 cm height and 20 cm width is installed at 15 cm downstream of the injection slit. A total of 936160 grids are used for the main-combustor flow passage, and 159161 grids for the cavity. The grids are clustered in the flow direction near the fuel injector and cavity, as well as in the vertical direction near the bottom wall. The no-slip and adiabatic conditions are assumed throughout the entire wall boundary. As a specific example, the inflow Mach number is assumed to be 3, and the temperature and pressure are 600 K and 0.1 MPa, respectively. Gaseous hydrogen at a temperature of 151.5 K is injected normal to the wall from a choked injector.A series of calculations were carried out by varying the fuel injection pressure from 0.5 to 1.5MPa. This amounts to changing the fuel mass flow rate or the overall equivalence ratio for different operating regimes. Figure 1 shows the instantaneous temperature fields in the supersonic combustor at four different conditions. The dark blue region represents the hot burned gases. At the fuel injection pressure of 0.5 MPa, the flame is stably anchored, but the flow field exhibits a high-amplitude oscillation. At the fuel injection pressure of 1.0 MPa, the Mach reflection occurs ahead of the injector. The interaction between the incoming air and the injection flow becomes much more complex, and the fuel/air mixing is strongly enhanced. The Mach reflection oscillates and results in a strong fluctuation in the combustor wall pressure. At the fuel injection pressure of 1.5MPa, the flow inside the combustor becomes nearly choked and the Mach reflection is displaced forward. The leading shock wave moves slowly toward the inlet, and eventually causes the combustor-upstart due to the thermal choking. The cavity appears to play a secondary role in driving the flow unsteadiness, in spite of its influence on the fuel/air mixing and flame evolution. Further investigation is necessary on this issue. The present study features detailed resolution of the flow and flame dynamics in the combustor, which was not typically available in most of the previous works. In particular, the oscillatory flow characteristics are captured at a scale sufficient to identify the underlying physical mechanisms. Much of the flow unsteadiness is not related to the cavity, but rather to the intrinsic unsteadiness in the flowfield, as also shown experimentally by Ben-Yakar et al. [6], The interactions between the unsteady flow and flame evolution may cause a large excursion of flow oscillation. The work appears to be the first of its kind in the numerical study of combustion oscillations in a supersonic combustor, although a similar phenomenon was previously reported experimentally. A more comprehensive discussion will be given in the final paper presented at the colloquium.

• 한국음향학회지
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• 제24권3호
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• pp.171-177
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• 2005

본 논문에서는 콘서트홀에서 확산체의 Early Stage Support (ST1)에 대한 영향을 알아보기 위하여 1:25 축소모형에서 8지점을 설정하여 ST1을 측정하였다. 무대 바닥에 의한 영향을 살펴보기 위하여 흡음천의 유무에 따라 ST1의 결과값의 차이를 살펴보았다. 무대측벽에 대한 영향을 살펴보기 위하여 기존의 확산체, 확산체를 제거한 경우와 반구 확산체의 3가지 형태의 확산체를 사용하여 측벽의 변화에 의한 ST1 값의 결과를 살펴보았다. 결과적으로 무대 바닥에서의 흡음천의 사용은 ST1에서 고주파의 저감을 일으켰으나 평균값에는 큰 차이가 없었으며, 3가지 형태의 확산체는 뚜렷한 차이를 보이지 않았으나 측정 지점에 따라 ST1 값의 차이가 발생하였고, 특히 반구 확산체에서는 ST1 값이 고르게 분포하였다. 따라서 무대 바닥은 상대적으로 ST1의 변화에 큰 영향을 주지 않았고, 무대 측벽의 형상은 확산현상에 의해 ST1의 분포에 영향을 주었다.

• 자원환경지질
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• 제39권4호
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• pp.441-450
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• 2006

우리나라에서 최초로 육상탄성파탐사를 실시한 것은 1960년대 중반이다. 탄성파탐사와 관련된 최초의 보고저가 나온 것은 국립지질조사소의 김종수박사 등이 1964년 포항지역의 석유부존 가능성을 조사하기 위하여 수행한 반사법 탄성파탐사와 서울대학교의 현병구교수가 탄광의 갱도 주벽의 상태를 조사하기 위하여 실시한 굴절법탐사이다. 이후, 국립지질조사소 기본연구계획의 일환으로 경상계 퇴적분지의 층후 및 지질구조 조사를 위한 굴절법탐사가 실시되었다. 1970년대 들어서는 지하수조사, 광물자원탐사, 땅굴조사, 원자력 발전소 지반조사 등 탐사의 대상과 목적이 다양해졌으며, 1978년에는 CDP기법을 이용한 반사법탐사가 경상분지 지역에서 처음으로 실시되었다. 이후, 육상 탄성파탐사는 토목건설 분야에서 지반조사를 위한 굴절법탐사를 위주로 이루어지다가, 1990년대 들어서서 고해상반사법탐사와 탄성파토모그래피 및 다양한 시추공 탄성파탐사가 시도되었다. 이와 함께 응용분야도 단층대나 조간대와 같은 특정 지역에 대한 학술적 목적의 연구와 더불어 고속도로, 철도, 댐 건설 등 각종 토목엔지니어링, 지열과 광물 자원탐사, 매립지나 해수침투 지역 등의 환경영향 조사, 문화재 안전관리를 위한 고고학에의 응용 등 다양한 분야로 확대되었다. 2002년에는 한반도를 가로지르는 측선 상에서 지각규모의 탄성파탐사가 이루어져 육상탄성파탐사 연구의 새 장을 열게 되었다. 그 동안 우리나라 대륙붕과 해외 유전지역에서의 활발한 석유탐사를 통하여 이룩한 탐사기술의 자립화와 자료 처리를 위한 소프트웨어 부분에서 이룩한 기술적 발전은 앞으로 육상탄성파탐사의 활성화에도 크게 기여할 것으로 기대된다.

• 한국해안·해양공학회논문집
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• 제22권6호
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• pp.374-386
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• 2010

최근 슬리트케이슨제와 같은 유공방파제의 파랑제어특성에 대한 이론적 실험적 연구가 활발히 진행되고 있다. 본 연구에서는 규칙파의 작용하에 슬리트케이슨에 의한 반사율의 특성과, 전면유공부 및 유수실의 내부벽면에 작용하는 파압을 2차원 및 3차원수치파동수로에서 각각 추정하고, 그 결과를 검토하였다. 수치실험에서는 주기 7초, 9초, 11초 및 13초와 각각의 주기에 대해 파형경사 0.02, 0.03 및 0.04를 갖는 입사파고의 수치실험안을 설정하였고, 본 연구에서 사용된 2차원 및 3차원의 수치해석은 Navier-Stokes운동방정식에 기초한 이상류(이상류(二相流)) 수치 모델로서, 이는 타해석기법에 비해 복잡한 수면변동에 대한 물리현상을 쉽게 재현할 수 있으며, 수치프로그램의 구성이 보다 간략하게 되는 장점이 있다. 실험결과에 의하면, 반사율에 있어서 주기가 짧은 경우에는 2차원해석이 상당히 큰 값을 나타내지만, 주기가 길어지고 파형경사가 큰 경우에는 2차원해석과 3차원해석의 결과가 거의 동일한 값을 나타낸다. 파압에 있어서 주기가 짧은 경우에는 두 해석법에서 차이는 작지만, 주기가 길어지고 파형경사가 큰 경우에는 차이가 크게 나타나는 경향을 확인할 수 있었다.

• Journal of Electrical Engineering and Technology
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• 제10권1호
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• pp.314-319
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• 2015

The conventional geometry of a plate microstrip resonator is made up of a single metallic patch, which is printed on a monolayer dielectric substrate. Its arrangement is simple and easy to make, but it is limited in its functional abilities. Many searches have been realized to improve the bandwidth and the gain of the microstrip resonators. Among the various configurations proposed in the open literature, the stacked geometry seems to be very promising. By appropriate design, it is able to provide the operation in dual frequency mode, wide bandwidth enough and high gain. The theoretical investigations of structures composed of two stacked anti-reflection coatings, enhanced metallic coatings are available in the literature, however, for the stacked configurations involving three metallic coatings or more, not to exact or approximate analysis was conducted due to the complexity of the structure.

• 한국음향학회:학술대회논문집
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• 한국음향학회 2000년도 하계학술발표대회 논문집 제19권 1호
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• pp.439-442
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• 2000

When we measure the acoustical properties of a room using multiple microphone system, it is important to grasp exact time delay of the early reflections from impulse response pair. But it is often very difficult to identify the early reflections in natural shape, because a waveform may be deformed due to the characteristics of a sound source loudspeaker, microphone and reflected wall and overlapping of plural waveform. In this paper to obtain more accurate and enough early reflections, we propose the brand-new five-channel sound receiving system and introduce peak-detecting algorithm. The system has microphones mounted at the origin and four points of a regular tetrahedron. The newly introduced peak-detecting algorithm can show exact peak position in each channel, in spite of deformation due to reflected walls, loudspeaker and microphone.

• 대한수학회논문집
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• 제10권3호
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• pp.767-781
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• 1995

In this paper we present computation of a reflected shock in the hypersonic flow of air with chemical reactions. We consider two dimensional steady inviscid hypersonic flow of air around bodies including chemical reaction effects. At a high Mach number, a strong shock is formed in front of the body when a wedge is placed against the flow. In front of the shock, temperature and pressure increase greatly and the flow is in nonequilibrium state. If the shock hits a wall, then a reflected shock is formed in the nonequilibrium flow region. Behind this reflected shock, the temperature and pressure are very high. We carry out the computation of the reflected shock and the flow behind it. The jump conditions at the reflected shock are presented. A technique combining smooth transforms of domain and implicit difference methods is used to overcome numerical difficulties associated with the lack of resolution behind the shock and near the body.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2005년도 추계 학술대회논문집
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• pp.131-134
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• 2005

Conventional high order interpolation schemes are limitative in several aspects mainly because they need data of neighboring cells at the reconstruction step. However, discontinuous Galerkin method and spectral volume method, two high order flux schemes which will be analyzed and compared in this paper, have an important benefit that they are not necessary to determine the flow gradients from data of neighboring cells or elements. These two schemes construct polynomial of variables within a cell so that even near wall or discontinuity, the high order does not deteriorate.