• Proceedings of the Korean Society of Precision Engineering Conference
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• 2006.10a
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• pp.475-476
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• 2006

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.7
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• pp.12-17
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• 2006

Longitudinal static stability and steady aerodynamic characteristics of wings flying over nonplanar ground surfaces (rail and channel) are investigated using the boundary-element method. For a channel with it's fence higher than the wing height, the lift and the nose-down pitching moment increase as the gap between the wingtip and the fence decreases. For a rail with it's width wider than the wing span, the lift and the nose-down pitching moment increase as the rail height decreases. Longitudinal static stability of a single wing flying over nonplanar surfaces is worse than the case of the flat ground. In case of tandem wings, longitudinal static stability of the wings flying over the channel is better than the case of the flat ground. It is believed that the present results can be applied to the conceptual design of high-speed ground transporters.

• Proceedings of the Korean Vacuum Society Conference
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• 2013.02a
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• pp.520-520
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• 2013

Lateral 구조를 갖는 탄소나노튜브 에미터 캐소드의 금속전극 선폭과 간격은 탄소나노튜브 에미터 밀도와 게이트에 인가되는 전계의 크기에 밀접한 관계가 있어 전계방출특성에 큰 영향을 나타내므로 조속한 상업화를 위해서는 최적화 연구가 요구된다. 따라서 본 연구에서는 금속전극의 선폭과 간격을 110/30, 80/30, 40/30과 120/20, 90/20, 20/20 ${\mu}m$로 각각 변화시켜 4.6인치 탄소나노튜브 에미터 기반 flat light lamp 개발연구를 진행하였다. 이때 사용한 금속전극은 2 mm 두께를 갖는 4.6인치 소다라임 글라스 위에 패턴 된 PR에 Ag를 sputtering하여 증착 후 PR을 lift-off하여 형성하였다. 이와 같이 형성된 금속전극은 ~1 ${\mu}m$와 12 nm의 두께와 표면단차를 각각 가지고 있었다. 형성된 금속전극 위에 유전체와 탄소나노튜브 에미터를 각각의 페이스트를 사용하여 스크린 인쇄와 소성과정을 통해 형성하였다. 이때 레이저 빔을 전극사이의 빈 공간에 조사하여 탄소나노튜브 에미터를 금속전극 위에 정밀하게 정렬하였으며 잔존하는 유기물과 유기용매를 없애기 위해 대기압 공기분위기의 $410^{\circ}C$에서 10분간 소성과정을 거친 후 접착테이프를 사용하여 잔탄 속에 있는 탄소나노튜브 에미터를 물리적 힘으로 수직하게 노출시켜 캐소드를 준비하였다. 애노드는 전계에 의해 방출된 전자의 측정과 전계방출 이미지를 얻기 위해서 P22 형광체와 Al박막이 증착된 2 mm 두께의 소다라임 글라스를 사용하였다. 캐소드와 애노드 사이의 간격은 6~10 mm로 유지하였고, 진공챔버의 기본 압력을 $5{\times}10^{-6}$ Torr 이하로 유지하였다. 캐소드와 게이트 전극에 1, 4 kHz와 3% duty를 갖는 bipolar 형태의 DC 사각펄스파를, 애노드에 ~18 kV의 DC 고전압을 각각 인가하여 평가하였으며 추후, 이렇게 제작된 다양한 선폭과 간격을 갖는 탄소나노튜브 에미터 기반 flat light lamp의 전계방출특성과 효율에 대한 비교 연구를 진행할 계획이다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.9
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• pp.866-870
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• 2011

In this paper, the aerodynamic forces of a Korean Traditional Bangpae Kite with the wind hole and spanwise curved dihedral were measured by wind tunnel test. For the flat plate kite without the wind hole, the stall presents at ${\alpha}=35^{\circ}$ with $C_{Lmax}$=1.2. The Korean Traditional Bangpae Kite with the wind hole had $C_{Lmax}$=1.05 at ${\alpha}=30^{\circ}$ without the apparent stall phenomena. As the wind hole size growing, the lift and drag of kite were changed slowly after stalling angle of attack. As increasing the leading edge dihedral angle, lift curves were more increased than drag curves. As the growing of wind hole size, the effect of dihedral angle was constant affect to the lift and drag of kite.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.3
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• pp.14-21
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• 2006

The unsteady vortex lattice method is used to model twisting and flapping motions of a rectangular flat plate wing. The results for plunging and pitching motions were compared with the limited experimental results available and other numerical methods. They show that the method is capable of simulating many of the features of complex flapping flight. The lift, thrust and propulsive efficiency of a rectangular flat plate wing have been calculated for various twisting angles and reduced frequency with an amplitude of flapping angle($20^{\circ}$). And the effects of the twisting on the aerodynamic characteristics of the flapping wing are discussed by examination of their trends.

• International Journal of Aeronautical and Space Sciences
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• v.14 no.3
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• pp.229-236
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• 2013

This paper presents the experimental investigation of a biplane micro air vehicle. The effects of geometric parameters, gap, stagger, and decalage angle are investigated at low Reynolds number (~150,000) in a low-speed wind tunnel. A rigid flat plate with an aspect ratio of one and square planform shape is used to evaluate all three geometric parameters. The side dimension of the single flat plate is 0.15 m. The goal is to find an optimal biplane configuration that should exceed monoplane performance by generating high lift and flying as slow as possible, in order to capture high-quality visual recordings. This configuration will directly help to fly at a lower velocity and to make tighter turns that are advantageous in restricted environments. The results show that the aerodynamic performance of the biplane MAV is significantly enhanced through the combination of gap and stagger effects. A performance comparison demonstrates the superiority of the optimal biplane configuration compared to a monoplane in cruise and glide phases. Moreover, no significant compromise is found for the range, endurance, and climb performance.

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.5
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• pp.67-72
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• 2008

The film cooling effectiveness on a flat plate measured by pressure sensitive paint technique. Six film cooling hole were fabricated on a flat plate with 30 degree angle with respect to the surface and three blowing ratios of 0.5, 1, and 2 were tested. Results showed that PSP technique successfully evaluated the distribution of film cooling effectiveness and showed similar results with references. The film cooling effectiveness near the film cooling holes was higher for lower blowing ratio case. As the blowing ratio was increased, the film cooling effectiveness near the film cooling hole decreased due to the lift off of the coolant. At far downstream, the film cooling effectiveness for higher blowing ratio was higher due to the coolant reattachment.

• Journal of Advanced Marine Engineering and Technology
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• v.25 no.5
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• pp.1091-1097
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• 2001

A numerical investigation was performed to determine the effect of airfoil on the optimum flap height using NACA 00XX and 44XX airfoils. The six flaps which have 0.5% chord height difference were selected . A Navier-Stokes code, FLUENT, was used to calculate the flow field of the airfoil. The code was first tested as a benchmark by modelling flow around a NACA 4412 airfoil. Predictions of local pressure coefficients are found to be in good agreement with the result of the experimental results. For every NACA 00XX and 44XX airfoil, flap heights ranging from 0.0% to 2.5% chord were changed by 0.5% chord interval and their effects were also studied. Representative results from each case are presented graphically and discussed. It is conclued that this initial approach gives an idea for the future development of the wind turbine optimum design.

• Journal of computational fluids engineering
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• v.20 no.3
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• pp.47-53
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• 2015

This study performed numerical simulation to elucidate the characteristics of flow past a rectangular cylinder with various values of the aspect ratio(AR) of the cylinder. We calculated the flow field, force coefficients and Strouhal number of vortex shedding depending on the Reynolds number(Re) and the aspect ratio. The $AR{\approx}1$ is preferred for drag reduction, and 0.375$AR{\approx}0$ is recommended if suppression of the lift-coefficient fluctuation and the shedding frequency is desirable. Furthermore the criticality of the Hopf bifurcation is also reported for each AR.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.28 no.12
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• pp.1511-1520
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• 2004

A flow visualization of the two-dimensional rigid fling-clap motions of the flat-plate wing are performed to gain knowledge of butterfly mechanisms that might be employed by butterflies during flight. In this numerical visualization, the time-dependent Navier-Stokes equations are solved for cyclic fling and clap types of wing motion. The separation vortex pair that is developed in the fling phase of the cyclic fling and clap motion is observed to be stronger than those of the fling followed by clap and pause motion(1st cycle motion). This stronger separation vortex pair in the fling phase is attributable to the separation vortex pair of the outside space developed in the clap phase as it moves into the opening in the following fling phase. Accordingly, higher lift and power expenditure coefficients in the fling after clap phase is caused by the stronger separation vortex pair.