• 한국항공우주학회지
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• 제30권3호
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• pp.57-63
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• 2002

지면효과를 받는 와류면의 2차원 비정상 전개를 이산와류법을 사용하여 연구하였다. 와류면이 말리는 정확한 형상을 얻기 위하여, 두 개의 평활기법을 비교하였다. 타원형 하중분포를 가지는 지면가까이에 있는 날개의 후류말림에 대하여 본 연구 방법을 적용하였다. 날개가 지면가까이 비행할 때, 지면효과로 인하여 와류가 날개길이방향으로 이동하였으며 날개익단부근에서 와류면의 늘림운동이 발생하였다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2002년도 추계 학술대회논문집
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• pp.47-52
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• 2002

We present an improved Lagrangian vortex method in 2-D incompressible unsteady viscous flows, which is based on a mesh-free integral approach of the velocity-vorticity formulation. Vorticity fields are represented by discrete vortex blobs that are updated by the Lagrangian vorticity transport with the particle strength exchange scheme. Velocity fields are expressed in a form of the Helmholtz decomposition, which are calculated by a fast algorithm of the Biot-Savart integration with a smoothed kernel and by a well-established panel method. No-slip condition is enforced through viscous diffusion of vorticity from a solid body into field. The vorticity flux is determined in such a way that spurious slip velocity vanishes. Through the comparison with the existing finite volume scheme for the transient vortical flows around an impulsively started cylinder at Reynolds number Re=550, we would obtain a more accurate scheme for vortex methods in complicated flows.

• 대한조선학회논문집
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• 제30권3호
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• pp.62-74
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• 1993

균일한 정상유동을 하는 유체 안에 가로놓인 원주로부터 일어나는 vortex유출을 이산 vortex 방법을 써서 vortex cloud모형으로 simulation했다. 원주표면에서 생겨나는 와도를 매 시간 간격마다 미리 정해진 많은 갯수의 이산화된 초생 vortex로 나타낸 후 기 유출된 vortex들에 합류시켜 누적된 vortex들의 운동을 탐색함으로서 vortex 분포 상태의 진화를 알아낸다. vortex들의 이동은 cloud-in-cell 기법을 써서 추적 하였고 항력 계수와 양력 계수는 Sarpkaya의 식과 Lee의 식을 써서 계산하여 실험치와 비교하였다. 계산 인수 사이의 상호 연관 관계를 논고하였으며 부분적이나마 적정값 선정 원칙을 제시하였다.

• Journal of Advanced Marine Engineering and Technology
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• 제29권7호
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• pp.769-778
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• 2005

The velocity and pressure fields of a ship's Weis-Fogh type propulsion mechanism are studied in this paper using an advanced vortex method. The wing (NACA0010 airfoil) and channel are approximated by source and vortex panels. and free vortices are introduced away from the body surfaces. The viscous diffusion of fluid is represented using the core-spreading model to the discrete vortices. The velocity is calculated on the basis of the generalized Biot-Savart law and the pressure field is calculated from an integral, based on the instantaneous velocity and vorticity distributions in the flow field. Two-dimensional unsteady viscous flow calculations of this propulsion mechanism are shown. and the calculated results agree qualitatively with the measured thrust and drag due to un-modeled large fluctuations in the measured data.

• Journal of Mechanical Science and Technology
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• 제20권8호
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• pp.1248-1255
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• 2006

The velocity and pressure fields of a ship's propulsion mechanism of the Weis-Fogh type, in which a airfoil moves reciprocally in a channel, are studied in this paper using the advanced vortex method. The airfoil and the channel are approximated by a finite number of source and vortex panels, and the free vortices are introduced from the body surfaces. The viscous diffusion of fluid is represented using the core-spreading model to the discrete vortices. The velocity is calculated on the basis of the generalized Biot-Savart law and the pressure field is calculated from integrating the equation given by the instantaneous velocity and vorticity fields. Two-dimensional unsteady viscose flows of this propulsion mechanism are numerically clarified, and the calculated results agree well with the experimental ones.

• Journal of Advanced Marine Engineering and Technology
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• 제22권3호
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• pp.371-380
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• 1998

The flow patterns and dynamic properties of ship's propulsion mechanism of two-stage Weis-Fogh type are studied by the discrete vortex method. In order to study the effects of the interaction of the two wings two cases of the phase differences of the wing's motion are considered the same phase and the reverse phase. The flow patterns by simulations correspond to the photographs obtained by flow visualization and flowfield of the propulsion mechanism which is unsteady and complex is clearly visualized by numerical simulations. The time histories of the thrust an the drag coefficients on the wings are also calculated and the effects of the interaction of the two wings are numerically clarified.

• 대한기계학회논문집
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• 제17권2호
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• pp.426-437
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• 1993

The flowfield of Weis-Fogh type ship's Propulsion is visualized by numerical simulations using the discrete vortex method and by the hydrogen bubble technique. The simulations are performed by assuming that the separations occur at the trailing edge of the wing. The streak lines and time lines are calculated by introducing the tracers at adequate intervals. They agree well with experimental results. The flowfield is unsteady and complex, but the properties of the flow are clarified by numerical and experimental visualization.

• 대한기계학회논문집B
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• 제21권11호
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• pp.1518-1526
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• 1997

The dynamic properties of a ship's propulsion mechanism of Weis-Fogh type are studied by the discrete vortex method. The wing in the channel is approximated by a finite number of bound vortices and free vortices representing the separated flow are introduced from the trailing edge of the wing. The time histories of the thrust, the drag, and the moment acting on the wing are calculated, including the unsteady force due to the change of strength of the bound vortices. These calculated results show a similar tendency to the experimental ones qualitatively and the dynamic properties of this propulsion mechanism are numerically clarified.

• 한국마린엔지니어링학회:학술대회논문집
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• 한국마린엔지니어링학회 2006년도 전기학술대회논문집
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• pp.279-280
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• 2006

In the present study the flow fields around pitching foils have been visualized by using a Schlieren method with a high speed camera in a wind tunnel at low Reynolds number regions. It has been observed that small vortices are shed discretely from the leading and trailing edge and that they stand in line on the integrated streakline of separation shear layer. By counting vortices in the VTR frames it was clarified that the number of vortex shedding from the leading and trailing edge during one pitching cycle strongly depends on the non-dimensional pitching rate.

• 대한조선학회지
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• 제20권1호
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• pp.35-46
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• 1983

The hydrodynamic lift and moment acting on the bodies of revolution with pointed-end were calculated by the surface discrete vortex method. It was found, by direct computation, that the lift normal to the on-coming flow can be generated by introducing the shed-vortex to the unless otherwise purely potential model. The value of the destabilizing moment, which is called Munk moment, is reduced by the shed-vortex model, resulting in better agreement with the existing experimental values.