• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.1
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• pp.18-26
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• 2007

The steady-state aerodynamic characteristics of wings on the formation flight were analyzed using the Vortex Lattice Method. When two wings were at formation flight, the sectional lift coefficient of a rear wing was increased due to a front wing. The result showed that the lift drag ratio increased as the rear wing were placed downward and decreased as the lateral spacing between wings increased. The difference of lift drag ratio between forward wing and rear wing increase as the aspect ratio of wings increased. When a rear wings and a forward wings placed at the same height, wings on the formation flight had the maximum lift drag ratio. The results showed that the benefit of the formation flight increased as the number of wings on the formation flight increased.

• Aerospace Industry
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• v.40
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• pp.54-57
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• 1996

날개비행기인 B-2 폭격기가 취역한데 이어 이번에는 꼬리날개가 없는 X-36이라는 미래형 전투기가 축소형 모형으로 만들어져 방금 지상시험이 진행중에 있어 세계 항공기 개발업계에 비상한 관심이 모으고 있다. 미국의 NASA와 MD사가 반반씩 비용을 부담하여 개발한 미래형 전투기의 기선을 제압할 X-36의 이모 저모를 알아본다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.257-265
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• 2009

The present study deals with the leading edge shape on a wing-body junction to decrease a horseshoe vortex, one of the main factors to generate the secondary flow losses. The shape of leading-edge is optimized with design variables form the leading-edge shape. Approximate optimization design method is used for the optimization. The study is investigated using $FLUENT^{TM}$ and $iSIGHT^{TM}$. As the result, total pressure coefficient of the optimized design case was decreased about 9.79% compare to the baseline case.

• Journal of the Korean Society of Propulsion Engineers
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• v.13 no.6
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• pp.24-33
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• 2009

The present study deals with the optimization of the leading edge shape around a wing-body junction to minimize the strength of the horseshoe vortex, which is one of the main factor generating the secondary flow losses. For this purpose, approximate optimization method is used for the optimization. The study is performed by using $FLUENT^{TM}$ and $iSIGHT^{TM}$. The total pressure coefficient for the optimized model was decreased about 9.79% compared with the baseline model.

• The Korean Journal of Soil Zoology
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• v.7 no.1_2
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• pp.23-28
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• 2002

In the course of taxonomical studies of oribatid mites, eight species, Tenuiala nuda Ewing, 1913, Cosmopirnodus angulatus Ichisawa and Aoki, 1998, Neoribates pallidus Aoki, 1988, Belba sellnicki Bulanova-Zachvatkina, 1962, Camisia horrida (Hermann 1804), Hermannia gibba (C. L. Koch 1839), Eueremaeus elongatus (Fujikawa 1972), and Licnodamaeus undulatus (Paoli 1908) are recorded from Korea for the first time.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.8
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• pp.747-757
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• 2010

The ice accreted on the airfoil is one of the critical drivers that causes the degradation of aerodynamic performance as well as aircraft accidents. Hence, an efficient numerical code to predict the accreted ice shape is crucial for the successful design of de-icing and anti-icing devices. To this end, a numerical code has been developed for the prediction of glaze ice accretion shape on 2D airfoil. Constant Source-Doublet method is used for the purpose of computational efficiency and heat transfer in the icing process is accounted for by Messinger model. The computational results are thoroughly compared against available experiments and other computation codes such as LEWICE and TRAJICE. The direction and thickness of ice horn are shown to yield similar results compared to the experiments and other codes. In addition, the effects of various parameters - temperature, free-stream velocity, liquid water contents, and droplet diameter - on the ice shape are systematically analyzed through parametric studies.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.9
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• pp.829-836
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• 2009

3-Dimensional flow which is represented by horseshoe vortex is generated as a type of secondary flow about the main flow. As well, it causes the flow loss. The present study deals with the leading edge fence shape on a wing-body junction to decrease a horseshoe vortex, one of the main factors to generate the secondary flow losses. The shape of leading-edge fence was optimized with the design variables of the installed height, length, width, and thickness of the fence as the design variables. Approximate optimization design method is used as the optimization. The study was investigated using $FLUENT^{TM}$ and $iSIGHT^{TM}$. Total pressure coefficient of the optimized design case was decreased about 7.5 % compare to the baseline case.

• Animal Systematics, Evolution and Diversity
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• v.12 no.2
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• pp.107-119
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• 1996

The tribe Quediini from Korea is examined. One new species, Velleius circumipectus, and one new subspecies, Quedius japonicus sachonensis, are described, and four species, Heterothops rotundiceps, Q. japonicus (s. str.), Q. simulans, and V. setosus, are recorded firstly in Korea. As a result, Korean fauna of the tribe Quediini comprises 10 species and one subspecies belonging to three genera.

• Korean journal of applied entomology
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• v.47 no.4
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• pp.487-490
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• 2008

Field collected larvae inside the pumpkin fruit in Jinan, Chonbuk Province were kept in the laboratory at $24{\pm}2^{\circ}C$, RH $65{\pm}5%$, and 14L:10D until they pupated and eclosed. Adults were fed with dry-milk based diet. Mating behavior was observed when they were 40 days old in a field cage at dusk in July and October, 2008. Wing vibration in male took place under the light intensity of 200 lux-20 lux, however, most commonly under 30 lux. Mounting between male and female was observed under 150 lux-30 lux after the act of wing vibration, also most frequently under 30 lux. Copulation occurred under 150 lux-20 lux. Females approached face to face to males which had been engaged in wing vibration and the copulation was successful for up to 64%. Copulation never occurred when a female positioned in front or at side of the male that was not engaged in wing vibration.

• Journal of the Korean Society of Propulsion Engineers
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• v.2 no.2
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• pp.14-23
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• 1998

The present study investigates numerically particle laden flow through compressor cascade. In general, a lot of turbine engines are affected by various particles which are suspending in the atmosphere. Especially in the case of aircraft aviating in volcanic, industrial and desert region including many particles, each components of engine system are damaged severely. That damage modes are erosion of compressor binding and rotor path components, partial or total blockage of cooling passage and engine control system degradation.. Initial damages can not be serious but cumulation of damages influences on safety of aircraft control and economical maintenance cost of engine system can be increased. When dust, materials and volcanic particles in the atmosphere flow in the compressor, it is necessary to predict damaged and deposited region of compressor blades. To the various flow inlet angle, predictions of particles trajectory in compressor cascade by Lagrangian method are presented and impulses by impaction of particles at blade surface are calculated. By the definition of particle deposition efficiency, characteristics of particles impact are considered quantitatively. With these prediction and experimental data, erosion rates are predicted for two materials - ceramic, soft metal - on compressor blade surface. Improvements like coating of blade surface could be found, by above prediction.