• Journal of Ship and Ocean Technology
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• 제11권3호
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• pp.39-50
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• 2007

This study aims the observation of wing-in-ground effect near free surface. Numerical computations are carried out to observe the deformation of free surface and the effects on lift and drag. The detailed flow fields around two- and three-dimensional wings with NACA 0012 section are observed from the results of a commercial CFD program, FLUENT, and the local deformations of free surface are obtained by applying a Rankine panel method. In the present cases, the small deformation of free surface under the wings is observed, but different forces are found between solid wall and free surface when the speed of wings becomes large.

• 시스템엔지니어링학술지
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• 제5권1호
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• pp.57-65
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• 2009

The purpose of Defense Acquisition Project is that the superior weapons validated needs and performance are supplied to military user with limited financial resources and time. The Warship Acquisition Project is not only like this, But also has special characteristics of long project period and first-constructed ship's operation employment. So, The Warship Acquisition Project need systematic and efficient procedure & management. And this paper researches System engineering application of imaginary WIG(Wing-In-Ground Effect) ship acquisition project based Systems Engineering Handbook ver.3.1 published by INCOSE, the lead of field. The Imaginary WIG(Wing-In-Ground Effect) ship acquisition project applied the four processes(technical project, Enterprise & Agreement, Enabling Systems), the basis of INCOSE Engineering Handbook ver.3.1, and the each process output compared with DAPA(Defense Acquisition Program Administration)'s warship acquisition procedure.

• 한국정밀공학회:학술대회논문집
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• 한국정밀공학회 2008년도 춘계학술대회 논문집
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• pp.211-212
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• 2008

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2005년도 춘계 학술대회논문집
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• pp.57-64
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• 2005

Aerodynamic characteristics of three-dimensional wings in ground effect for Aero-levitation Electric Vehicle(AEV) are numerically investigated for various fairing shapes at the junctions of 3D Wings. Numerical results show that a sizeable three-dimensional comer flow separation occurs with formation of an arch vortex at the junction of main and vertical wings, and also that this is predicted the main cause of the high lift-to-drag(L/D) reduction rate of the main wing. To avoid the comer flow separation, the main idea of this study is to reduce the cross section gradient of the comer flow tube near the trailing edge for various fairing shapes. Improvements on L/D ratios of the wings are pursued by breaking the coherence of superimposed adverse pressure gradients at the wing junction when the cross section gradient is changed slowly at the trailing edge.

• 한국지구물리탐사학회:학술대회논문집
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• 한국지구물리탐사학회 2003년도 Proceedings of the international symposium on the fusion technology
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• pp.103-108
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• 2003

In the construction of mountain tunnels, reaction forces of the legs of steel arch supports against the ground are often expected to support the ground being excavated. In these cases, a stress concentration occurs in the ground directly under the support legs. If the bearing capacity of the ground is insufficient or displacement is not effectively constrained, the local failure of the ground under the support legs or settlement of the tunnel supports due to large deformation could result. It is therefore necessary to reinforce the support legs to reduce settlement. As a means of reducing settlement, wing-ribbed steel arch supports are well used. In this study, with the aim of finding a way to quickly reduce the settlement of steel arch support legs, effectiveness of a new type of wing ribs to reinforce steel arch supports was investigated through laboratory testing.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2003년도 춘계학술대회
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• pp.1724-1729
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• 2003

A new ground transportation system is often simulated by the wing in ground effect(WIG). Recently, several kinds of experimental and computational studies are being carried out to investigate the WIG aerodynamic characteristics which are of practical importance to develop the new ground transportation vehicle system. These works are mainly based on conventional wind tunnel tests, but many problems associated with the WIG aerodynamic characteristics can not be satisfactorily resolved. In order to develop the new ground transportation vehicle system the WIG should be further investigated. To do this, it is necessary to develop a s imulator appropriate to the WIG aerodynamics. The objective of the present study is to clarify the aerodynamic characteristics of the WIG and to develop a new experimental test rig for the investigation of the WIG aerodynamics. Some preliminary experiments are performed to investigate the usefulness of the WIG simulator.

• 해양환경안전학회지
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• 제19권5호
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• pp.491-496
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• 2013

수면비행선박의 지위가 국제해사기구(IMO)에서 선박으로 분류하는 것으로 결론지은 이후, 국내외적으로는 몇몇 규칙과 권고 사항들이 개정 및 승인되었다. 하지만 정작 수면비행선박의 종류 및 운항특성을 고려한 항법에 관해서는 규정이 미비하고, 수면비행선박간 항법에 관련해서는 규정이 되어 있지 않다. 이러한 상황에서, 현행 법령상에 다른 선박들과 수면비행선박간의 책임 관계를 명확히 하기 위하여 서로 시계에 항법상의 수면비행선박 관련 규정을 모든 시계로의 항법상으로 이동할 것과 수면비행선박간 안전통항을 확보하기 위하여 타입 'B'와 'C'의 수면비행선박이 타입 'A'의 수면비행선박을 피항해야 한다는 규정이 신설되어야 한다고 판단된다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2005년도 춘계 학술대회논문집
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• pp.14-19
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• 2005

The paper introduces the state-of-the art of WIG ship and application field of the CFD to WIG ship development. WIG ships are highly efficient and fast transport vehicles which take advantage of benefits of ground effect. Chapter 1 describes the characteristics of WIG ship. Chapter 2 reviews the research works of Russia, German, Chinese, Korea and etc. Chapter 3 explains the kind of WIG ship categorized by the main operational mode and take-off system. Chapter 4 describes about the application field of CFD to WIG ship development procedure.

• 한국항공우주학회지
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• 제30권4호
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• pp.10-17
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• 2002

간접 경계요소법 (비정상패널법)을 사용하여 3차원 날개의 동적 지면효과에 대한 연구를 수행하였다. Green 정리를 사용하여 경계표면에 대한 적분방정식을 얻었다. 일정강도의 용출 및 용흡중첩을 날개표면에 분포시켰고 후류는 일정강도의 용흡중첩으로 나타내었다. 매 시간간격마다 한 행의 후류 패널들이 날개의 후연에서 하류로 대류한다고 가정하였다. 지면효과를 받는 날개의 익단 와류가 날개길이방향으로 이동하였다. 동적 지면효과를 받는 날개가 가지는 공력계수의 진폭 값이 정적 지면효과를 받는 날개의 경우보다 더욱 증가하였다.

• 한국항공우주학회지
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• 제35권6호
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• pp.483-488
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• 2007

경계요소법을 이용하여 동체에 탠덤 날개를 결합한 FAST가 비평면 지면을 비행할 때의 공력 특성을 파악하였다. 본 수치해석 기법을 이용하여 계산한 결과를 실험 및 타 전산해석 결과와 비교하여 검증을 수행하였다. 날개-동체를 결합한 운송체의 공력 특성을 분석하여 안정성 확보 및 충분한 공기부상력을 가지도록 운송체 상부의 탠덤 날개를 배치하는 공력설계를 수행하였다. FAST에서 탠덤 날개가 동체의 전두부와 후두부에 위치하고, 하단 익단판을 설치하였을 때 최대 양력 성능을 얻을 수 있었다. FAST의 안정성은 탠덤날개의 플래퍼론을 이용하여 확보 가능하다.