• Progress in Superconductivity
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• v.13 no.1
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• pp.7-11
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• 2011

The effects of Sm:Ba:Cu composition ratio in SmBCO coated conductor on their superconducting properties were investigated. The SmBCO coated conductors were fabricated by reactive co-evaporation method using EDDC(Evaporation using Drum in Dual Chamber) system. In this system, we could obtain various samples with different composition ratios in a batch by the technique providing composition gradient at deposition zone. From the specimens prepared by EDDC system, we found that composition ratio is uniform parallel to the drum axis, but gradient along the circumferential direction of the drum. We installed a shield having parallelogram open area between the deposition chamber and the evaporation chamber in EDDC system, and attached a 30 cm long template, which is parallel to drum axis, onto the drum surface. In this configuration, we could obtain SmBCO coated conductors having a gradient composition along the length of template. We measured the composition ratios and surface morphologies with periodic interval by SEM and EDAX, and confirmed the profile of composition ratio. We also measured critical current using non-contact Hall probe critical current measurement system and thereby could plot composition ratio vs. critical current. The maximum critical current was obtained, and the surface morphology with the shape of roof tile was observed at the corresponding composition ratio of Sm:Ba:Cu = 1.01:1.99:4.87. It was also found that composition ratio had an effect on not only critical current but also surface morphology.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.8
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• pp.641-648
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• 2016

In this study, the effect of injection nozzle shape on the supersonic film cooling performance is analyzed using CFD. The design parameters are inside and outside angles of upper plate of nozzle and nozzle tip thickness. It is observed that the mass flow rate of film cooling decreases with increase of inside angle, while the effect of the change of mass flow rate on the film cooling effectiveness is relatively small. In addition, cooling performance is generally reduced, except ahead of the local region where shock wave interaction with film cooling occurs, in accordance with the growth of the outside angle and tip thickness. In this paper, the CFD simulation is performed using a commercial software, ANSYS Fluent V15.0, and the CFD model is validated by comparing it with the experimental data shown in preceding research.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.7
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• pp.655-660
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• 2007

A canard-leading edge flap deflection scheduling laws have been established to enhance the maneuverability of the canard type fighter class aircraft. These scheduling laws are the relation of canard-leading edge flap deflections and flight conditions to maximize the lift-drag ratio. For these purposes, the corrected supersonic panel method has been used to predict the lift-drag characteristics due to canard-leading edge flap deflections. In addition, the high speed wind tunnel test has been conducted with 1/20 scale model to validate the predicted scheduling laws. Good agreements have been obtained compared with the results of high speed wind tunnel test. Based on the results obtained from the experimental and numerical studies, the corrected supersonic panel method has shown to be useful to establish the canard-leading edge flap deflection scheduling law for the aerodynamic design of canard type fighter class aircraft.

• Journal of Korean Society of Steel Construction
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• v.10 no.1 s.34
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• pp.73-83
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• 1998

Considering dynamic behaviors according to initial tension forces, geometric nonlinearity and the effect of higher eigen modes to participate in dynamic behaviors increase as initial tension forces decrease, and from phase portrait we can realize that period attractors are produced in many area with complexity. If initial tension forxes increase, difference between linear and nonlinear solutions will decrease and the first eigen mode dominate the dynamic behaviors and observing phase portrait, period attractors appear in certain area regularly. These results may offer meaningful informations to nonlinear dynamic analysis using modal reduction methods such as Lanczos modal analysis. And actually nonlinear dynamic analysis needs very large computational efforts. So, if we determine the number of eigen modes to take part in modal analysis corresponding to initial tension forces we will get more accurate data close to exact nonlinear dynamic solutions.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.5
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• pp.476-482
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• 2009

The effect of pintle shape on the thrust level of pintle-nozzle Solid Rocket Motor(PNSRM) was studied numerically using the Spalart-Allmaras turbulent model of Fluent. Mass flow rate of PNSRM was always less than theoretical value and the extent of decrease in mass flow rate grew in the large pintle because of increase in the relative boundary layer thickness between pintle body and nozzle wall. The bigger pintle size was, the more thrust of pintle tip pressure was obtained. Meanwhile the more thrust of nozzle and chamber pressure decreased. Hence, total thrust of big pintle was less than a small pintle under same throat area condition. Specific impulse was relatively flat for all pintle shape.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.10
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• pp.68-74
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• 2005

Optimal shape of a typical ramjet intake is examined numerically to maximize the total pressure recovery. A response surface method is introduced to approximately predict its performance with respect to the design parameters over the each design domain. The first deflection angle of ramp, the area of inlet throat, and the diffuser angle are chosen as a design parameter. ANOVA is used to verify the trustability of the achieved response surface. The total pressure recovery of the optimum model, compared to that of the base model, is increased by 36%. The loss of viscosity through the diffuser is estimated less than 5%.

• Proceedings of the Korean Vacuum Society Conference
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• 2012.02a
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• pp.581-581
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• 2012

나노스케일에서의 자구체(magnetic domain), 자화벽(magnetic domain wall)에 대한 연구가 활발하게 진행되고 있으며 특히 자화벽의 위치를 임의로 제어할 수 있는 기술을 응용한 메모리 소자에 대한 연구가 활발하다. 반면에 이러한 연구에 필수적인 자구체, 자화벽 이미징 장비는 매우 미비한 상황이다. 이와 같은 자성이미징(magnetic domain image), 자화벽(magnetic domain wall)을 연구하는데 있어 가장 핵심적인 장비가 SEMPA(Scanning Electron Microscopy with Polarization Analysis)이다. 일반적으로 SEM의 경우 고 에너지 빔의 전자 빔을 주사 시키고 이때 발생되는 이차 전자의 수를 2차원상의 영역에 따라 달라지는 비로 형상을 측정하게 된다. 이때 전자의 수 뿐만 아니라 이들의 spin polarization을 측정할 수 있다면 형상뿐 만 아니라 표면에서의 스핀 상태를 동시에 측정할 수 있게 된다. 기 개발된 W-filament source를 이용한 SEMPA는 field emission source에 비하여 전자빔의 세기가 약하며 이차 전자의 수도 적어 spin polarization 감도가 현저히 떨어진다. 또한 초고진공($1{\times}10^{-10}torr$)에서 사용할 수 없어 측정시료의 contamination을 방지할 수 없다. 이러한 문제점들을 보안하기 위하여 field emission source를 이용한 FE-SEMPA를 개발 중이며 2차전자의 spin polarization감도를 증가시키기 위하여 monte carlo simulation과 전산시늉등울 통해 스핀 검출기를 개발 및 연구결과를 발표하고자 한다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.185-191
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• 2008

The aerodynamic losses so attributed to the endwall - usually termed secondary flow losses or secondary losses - can be as high as 30$\sim$50% of the total aerodynamic losses in a blade or stator row. Inlet guide vanes, with lower total turning and higher convergence ratios, will have smaller secondary losses, amounting to as much as 20% of total loss for an inlet stator row. These are important part for improving a turbine efficiency. The present study deals with a leading edge chamfer groove on a wing-body to investigate the vortex generation and characteristics of a horseshoe vortex with the installed height, and depth of the groove. The current study is investigated with $FLUENT^{TM}$.

• Proceedings of the Korean Institute of Electrical and Electronic Material Engineers Conference
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• 2008.11a
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• pp.163-163
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• 2008

반도체 소자가 고집적화 되고 고속화를 필요로 하게 됨에 따라, 기존에 사용되었던 알루미늄이나 텅스텐보다 낮은 전기저항, 높은 electro-migration resistance으로 미세한 금속배선 처리가 가능한 Cu가 주목받게 되었다. 하지만 과잉 디싱 현상과 에로젼을 유도하여 메탈라인 브리징과 단락을 초래할 있고 Cu의 단락인 islands를 남김으로서 표면 결함을 제거하는데 효과적이지 못다는 단점을 가지고 있었다. 특히 평탄화 공정시 높은 압력으로 인하여 Cu막의 하부인 ILD막의 다공성의 low-k 물질의 손상을 초래 할 수 있는 문제점을 해결하기 위하여 기존의 CMP에 전기화학을 결합시킴으로서 낮은 하력에서의 Cu 평탄화를 달성 할 수 있는 기존의 CMP 기술에 전기화학을 접목한 새로운 개념의 ECMP (electrochemical-mechanical polishing) 기술이 생겨나게 되었다. 따라서 본 논문에서는 최적화된 ECMP 공정을 위하여 I-V곡선과 CV법을 이용하여 active. passive. trans-passive 영역의 전기화학적 특징을 알아보았고. Cu막의 표면 형상을 알아보기 위해 Scanning Electron Microscopy (SEM) 측정과 Energy Dispersive Spectroscopy (EDS) 분석을 통해 금속 화학적 조성을 조사하였다.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.37 no.2
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• pp.161-170
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• 2013

The flow and combustion characteristics in a premixed swirl combustor with a double cone burner are numerically analyzed to adopt a swirler model. The internal recirculation zone formed at the burner exit can be realized by a swirler with inner and outer diameters of 56 and 152 mm, respectively, and accordingly, the flow rate and radial velocity were determined. To select the tangential velocity, swirl and recirculation angles are introduced. A tangential velocity of 40 m/s produces an internal recirculation zone similar to that in a combustor. At the liner exit, the errors in temperature and velocity are 2.8% and 0%, respectively, and they are negligibly small. However, NOx emissions are underestimated by 67% in the numerical results obtained using the swirler model. Although considerable quantitative errors are induced by the swirler model, it can be useful numerical model for the EV burner because it can approximately simulate the essential flow and combustion characteristics in a premixed swirl combustor with a double cone burner and it is expected to make combustion analysis efficient in a gas turbine combustor with complex geometries.