• 무역상무연구
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• 제54권
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• pp.45-80
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• 2012

Since the 9.11 terror attack, the event which caused supply chain disruption, supply chain security has become more important than ever before. With this as a momentum, a customs supply chain security paradigm emerged intended to guarantee secure flow of cargo across boarder. Under this circumstances Incoterms(R) 2010 rules have allocated obligations between the buyer and seller to obtain or to render assistances in obtaining security clearances. Thus, security related obligations such as providing advance manifest information is the mandatory requirements for any export and import. The impact on the seller and buyer of security related obligations under the Incoterms(R) 2010 rules environment is obvious. Assistance to provide the security information in advance has become indispensable obligations to the seller and buyer. As such assistances is at the cost and risk of the party responsible for the clearances of the goods, the choice of recognised partner and compliance with the relevant security program, in order to enjoy the relevant benefits, becomes paramount.

• 한국군사과학기술학회지
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• 제15권1호
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• pp.101-110
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• 2012

The side jet effects between jet flow and free-stream on a missile body were investigated by experimentally and numerically for modeling aerodynamic coefficients in pitch plane. K-factors for normal force and pitching moment were introduced to estimate the side jet effects. The main parameters of the jet interaction phenomena were angle of attack, jet pressure ratio, Mach number and jet bank angle. The K-factors for normal force coefficient and pitching moment coefficients in pitch plane were analysed.

• 한국해양공학회지
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• 제20권6호
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• pp.35-40
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• 2006

In recent years, there's been strong demand for seawalls that havea gentle slope and permeability that serveswater affinity and disaster prevention from wave attack. The aim of this study is to examine wave transformation, including wave run-up that propagates on the coastal structures. A numerical model based on the weak nonlinear dispersive Boussinesq equation, together with the unsteady nonlinear Darcy law for fluid motion in permeable layer, is developed. The applicability of this numerical model is examined through Deguchi and Moriwaki's hydraulic model test on the permeable slopes. From this study, it is found that the proposed numerical model can predict wave transformation and run-up on the gentle slope with a permeable layer, but can't show accurate results for slopes steeper than about 1:10.

• 대한기계학회논문집
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• 제18권7호
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• pp.1808-1817
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• 1994

Unsteady aerodynamic analysis of an aircraft is done using a frequency domian 3-D panel method. The method is based on an unsteady linear compressible lifting surface theory. The lifting surface is placed in a flight patch, and angle of attack and camber effects are implemented in upwash. Fuselage effects are not considered. The unsteady solutions of the code are validated by comparing with the solutions of a hybrid doublet lattice-doublet point method and a doublet point method for various wing configurations at subsonic and supersonic flow conditions. The calculated results of dynamic stability derivatives for aircraft are shown without comparision due to lack of available measured data or calculated results.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2003년도 춘계학술대회
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• pp.1447-1452
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• 2003

Vortex is very interesting flow phenomena on the heat transfer enhancement. In the present study, naphthalene sublimation technique is used to determine the average and local mass transfer coefficients on the flat plate with vortex generator. A parametric study with Reynolds number and angle of attack is carried out to investigate the heat transfer enhancement. The heat transfer coefficients on the flat plate with rectangular type and delta type vortex generator are compared with those of the flat plate without the vortex generator. Comparing heat transfer coefficients between rectangular type and delta type vortex generator, rectangular type vortex generator has much higher value than delta type vortex generator at the same condition.

• 한국정밀공학회:학술대회논문집
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• 한국정밀공학회 2001년도 춘계학술대회 논문집
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• pp.719-722
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• 2001

Paraglider has been used for a good air sports instrument by many people in the world though its short history. And manufacturers have improved it continuously. It has the great growth from the first model like parachute to the latest model that has the extreme speed, but we can improve it in more parts. In this paper, we will show the method which can improve its performance by using Axiomatic Approach.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2002년도 학술대회지
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• pp.107-110
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• 2002

The present study deals with CFD analysis of 'The vortex generators on plastic plate heat exchanger'. When a vortex generator is placed on the heat transfer surface, the flow gets more complex because it entails complicated three-dimensional flows such as separation, reattachment, and recirculation. CFX-5.4, a commercial code utilizing unstructured mesh, has been used as a computational method for solving RANS(Reynolds-Averaged Wavier-Stokes) equations, and the applied turbulence model is $k-{\varepsilon}$ model. In addition, those computational analyses were implemented under various conditions , with or without the vortex generator between two plates, the number, form and the size of vortex generator, and different attack of angle. From the calculated temperature, velocity and pressure distribution, vorticity, wall heat flux and so on under those conditions, this study shows the effect of vortex on heat transfer.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 추계학술대회논문집B
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• pp.616-621
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• 2001

A numerical investigation was performed to determine the effect of airfoil on the optimum flap height using NACA 0021 Wells turbine. The five double flaps which have 0.5% chord height difference were selected. A Navier-Stokes code, FLUENT, was used to calculate the flow field of the Wells turbine. The basic feature of the Wells turbine is that even though the cyclic airflow produces oscillating axial forces on the airfoil blades, the tangential force on the rotor is always in the same direction. Geometry used to define the 3-D numerical grid is based upon that of an experimental test rig. This paper tries to analyze the optimum double flap of Wells turbine with the numerical analysis.

• 한국유체기계학회 논문집
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• 제4권2호
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• pp.29-34
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• 2001

Experimental and numerical studies are conducted to investigate the flow field over a NACA0012 airfoil with ground effects. In experiment, the ground is simulated by a moving belt system. From the comparison between the experimental and numerical results, it is concluded that the velocity gradient over the ground plane causes the increments in pressure coefficient on lower surface of the airfoil and reduces the suction peak at the leading edge.

• EDISON SW 활용 경진대회 논문집
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• 제3회(2014년)
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• pp.521-526
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• 2014

현대에 이르러 초경량 무인 비행기에 대한 많은 연구가 진행되고 있다. 이러한 비행체는 저레이놀즈수 영역에서 사용되는 특성으로 인해, 경계층 내에서 박리현상과 난류영역으로의 천이 등과 같은 여러 복합적인 현상을 발생시킴으로써 비행체의 공력특성에 큰 영향을 미친다. Bumpy Airfoil은 저레이놀즈수 유동에서의 이와 같은 문제를 해결하기 위해 제안된 익형이다. 따라서 본 논문은 전산열유체해석 프로그램인 EDISON_전산열유체를 이용하여 Bumpy Airfoil 형상에 대한 공력특성을 연구하였고, 발생하는 양항비를 원 익형과 비교하였다. 비압축성 조건 내에서, 공력 성능 향상을 위한 Bumpy Airfoil의 형상 변수로 Bump 개수와 높이를 선정하여 받음각에 따른 유동장을 분석하고 양항비를 수치해석 및 고찰하였다.