• 에너지공학
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• 제12권3호
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• pp.197-206
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• 2003

본 연구에서는 다공성 세라믹 필터를 사용하는 집진장치에서 역세정 과정의 유동특성을 규명하고, 역세정 시스템 설계에 적용하기 위한 전산해석을 수행하였다. 주요 연구내용으로는 역세정 과정에서 중요한 변수인 노즐 직경, 노즐 팁의 위치, 다공성 세라믹 캔들필터의 투과율, 디퓨저 형상, 역세정 압력 등이 집진장치 내부에서의 속도분포, 압력분포 등 역세정 유동특성에 미치는 영향을 상세히 계산하여 역세정 시스템의 사양 설계에 활용할 수 있도록 하였다. 전산해석에는 상용의 FLUENT code를 사용하여 에너지 보존식을 포함한 압축성 축대칭 Navier-Stokes 방정식을 유한체적법 (Finite volume method)으로 해석하였다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2010년 춘계학술대회논문집
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• pp.195-200
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• 2010

Numerical investigation was conducted to study the effects of after-body configurations and nozzle lip on the PIFS(Plume Induced Flow Separation) and eat flux to the base face. Two dimensional and axi-symmetric non-equilibrium Navier-Stoke's solver with $k-{\omega}$ SST turbulence model was used to solve the launching vehicle type configuration with propulsive jet. The experimental result of Robert J. McGhee was compared with our computational results for code validation. Three types of the after-body configurations (Straight, Boat-tail, Flare type) were simulated for this study. And the nozzle lip effect was studies using the three types of base configurations same simulation conditions. As a result of numerical investigations, higher pressure ratio condition and boat-tail after-body configuration caused severe PIFS phenomenon but the flare type after-body configuration and low pressure ratio suppressed PIFS. Flare type after-body configuration and low pressure ratio case reduced heat flux to base face. The nozzle lip dispersed the heat flux widely along the base face and the nozzle lip.

• 대한기계학회논문집B
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• 제23권5호
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• pp.670-677
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• 1999

An analysis of generation and growth of multicomponent particles has been carried out to predict the size and composition distributions of particles generated in the Modified Chemical Vapor Deposition(MCVD) process. In MCVD process. scale-up of sintering and micro-control of refractive index may need the Information about the size and composition distributions of $SiO_2-GeO_2$ particles that are generated and deposited. The present work solved coupled steady equations (axi-symmetric two dimensions) for mass conservation, momentum balance. energy and species(such as $SiCl_4$, $GeCl_4$, $O_2$, $Cl_2$) conservations describing fluid flow. heat and mass transfer in a tube. Sectional method has been applied to obtain multi-modal distributions of multicomponent aerosols which vary in both radial and axial directions. Chemical reactions of $SiCl_4$ and $GeCl_4$ were included and the effects of variable properties have also been considered.

• 한국연소학회지
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• 제14권4호
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• pp.1-6
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• 2009

Analysis of the internal state of the blast furnace is necessary to predict and to control the operating conditions. Especially, it is important to develop models of the blast furnace to predict the cohesive zone because shape of the cohesive zone influences overall operating conditions of blast furnace such as gas flow, chemical reactions and temperature. Because many previous blast furnace models have assumed cohesive zone to be fixed, it was not possible to evaluate the shape change of cohesive zone in relation with operating conditions such as PCR, blast condition, and production rate. In this study, an axi-symmetric 2-dimensional steady state model is proposed to simulate blast furnace processes. In this model, cohesive zone is determined by the solid temperature. Finite volume method is employed for numerical simulation. To find location of the cohesive zone, entire calculation procedure is iterated until converged. Through this approach, shape of the cohesive zone, velocity and temperature within the furnace are predicted from the model.

• 한국추진공학회지
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• 제4권3호
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• pp.45-54
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• 2000

Ignition transient is a. very rapid process lasting only in the order of 100 milliseconds and therefore it is difficult to measure all relevant ballistic properties. Numerical simulation is thus useful to quantify some of these hard to measure flow and ballistic properties. One-dimensional model was employed to study the effects of aging using simplified aging scenarios for both N-H sustainer and booster motors. Also the effects of newly designed igniter on the ignition of N-H sustainer was simulated. Radiation effects could be significant in terms of energy flux increase to the propellant surface and the energy exchange between the combustion gas itself. One dimension implementation of radiation showed significant effects for rear-mounted igniter. Implementation of radiation effects into 2-D axi-symmetric numerical model was completed and its effects on the N-H sustainer were examined. To have a reliable prediction of computer model on ignition transient, accurate chemical property data on the propellant and igniter gas are required. It was found that such property data on aged N-H motors are not available. Chemical aging model can be used to predict to some degree of accuracy effects of aging on chemical and mechanical properties. Such a model was developed, albeit 2-dimensional, to study migration of moisture through a representative solid rocket motor configuration.

• International Journal of Aeronautical and Space Sciences
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• 제18권2호
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• pp.352-364
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• 2017

A novel 3D mathematical model for water film runback and icing on a rotating surface is established in this work, where both inertial forces caused by the rotation and shear forces due to the air flow are taken into account. The mathematical model of the water film runback and energy conservation of phase transition process is established, with a cyclical average method applied to simulate the unsteady parameters variation at angles of attack. Ice accretion on a conical spinner surface is simulated and the results are compared with the experimental data to validate the presented model. Then Ice accretion on a cowling surface is numerically investigated. Results show that a higher temperature would correspond to a larger runback ice area and thinner ice layer for glaze ice. Rotation would enhance the icing process, while it would not significantly affect the droplet collection efficiency for an axi-symmetric surface. In the case at angle of attack, the effect of rotation on ice shape is appreciable, ice would present a symmetric shape, while in a stationary case the shape is asymmetric.

• 한국항공우주학회지
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• 제30권6호
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• pp.78-83
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• 2002

고속 열차가 터널을 통과할 때 열차 주위와 터널 내부에 발생하는 비정상 유통장을 규명하기 위해서 향상된 겹침 격자기법과 Roe의 FDS를 사용한 축대칭 Euler Solver를 개발하였다. 혼합차원기법이라는 새로운 영역기법을 개발하여 열차와 터널의 상호작용을 해석하는데 적용하였으며, 이 기법은 공간 차원의 최소 가정을 통해서 수치 계산의 효율성을 극대화하는 것에 목적을 두고 있다. 향상된 겹침 격자기법에 개발된 혼합차원기법을 추가하면 완전한 축대칭 방법과 거의 동일한 수준의 수치 정확도를 얻을 수 있다. 혼합차원기법은 특히 긴 터널에서 열차와의 상호작용을 해석할 때 높은 수치적 이득을 얻을 수 있다.

• 한국항공우주학회지
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• 제30권2호
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• pp.1-11
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• 2002

본 연구에서는 특별히 PC cluster와 같은 병렬 환경에서 효율적인 계산을 수행할 수 있는 격자중심에 기초한 직접모사 기법을 개발하였다. 병렬환경 하에서의 효과적인 계산 수행을 위해서는 전체 계산 영역을 격자수와 각 격자에 할당되는 모사 입자 수를 고려한 부 영역들로 나누어주었다. 또한, 격자 사용의 효율성 증대를 위해서는 매우 성긴 격자에서부터 출발하여 점차적인 격자 적응을 수행하였다. 본 방법은 2차원의 초음속 평판 문제와 축대칭의 Rothe, 노즐 문제에 적용하였다. 그 결과로부터 본 방법을 사용하면 기존의 입자 중심 기법에 비해 매우 효율적으로 희박기체 유동을 해석할 수 있음을 알 수 있었다.

• 한국항공우주학회지
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• 제30권5호
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• pp.24-31
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• 2002

축 대칭 원형노즐 출구에 삼각형 형태의 작은 탭이나 얇은 테이프가 부착되었을 때 나타나는 초음속 제트유동장의 변화에 관한 연구가 쉴리렌 영상과 피토압력 측정을 통하여 수행되었다. 노즐 출구면적의 1 %에 해당하는 작은 탭에서 나타나는 유동방향 와류에 의한 제트유동 변화는 유동이 과소팽창 될 때 완전팽창과 과대팽창의 경우에 비하여 더 크게 나타나며 이로 인한 유동유입이 더 크게 나타남을 알 수 있었다. 탭의 설치각도 변화에 의한 영향도 평가되었으며, 유동이 과대팽창 될 때 노즐 안으로 구부러진 탭의 설치가 충격파의 간섭강도를 약화시키고 이로 인한 마하디스크의 소멸현상을 관찰할 수 있었다. 아울러 노즐내부 낮은 높이의 돌출부가 후방 유동장의 원주방향으로 압력변화를 나타내고, 이러한 압력변화는 유동의 팽창 정도에 영향을 받음을 알 수 있었다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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• pp.634-643
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• 2004

In this paper are presented a concept of a new supersonic air inlet, which is designated a Multi-Row Disk (MRD) inlet, aiming at performance improvement under off-design conditions, and results of wind tunnel tests examined performance characteristics of the MRD inlet. The MRD inlet is frequently called ‘a skeleton inlet’ because of its appearance. The performance of a conventional axisymmetric inlet with a solid center body (spike) deteriorates under off-design Mach number conditions. It is due to the fact that total pressure recovery (TPR) governed by the throat area of inlet and mass capture ratio (MCR) governed by an incidence position of an oblique shock from the spike tip into the cowl can not be controlled independently in such air inlet. The MRD inlet has the spike that is composed of a tip cone and several disks arranged downstream of it, based on the experimental fact that several deep cavities on a conical surface have little negative effect on the boundary layer growth. The overall spike length of the MRD inlet is adjustable to the given flight speed by changing space between disks so that a spillage flow can be controlled independently from controlling the throat area. It could be made clear from the result of wind tunnel tests that the MRD inlet improves TPR by 10% compared with a conventional inlet with a solid spike under off-design conditions.