• 한국전산유체공학회지
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• 제14권3호
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• pp.76-85
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• 2009

The shock wave is deformed and the vortex is elongated simultaneously during the shock-vortex interaction. More precisely, the shock wave is deformed to a S-shape, consisting of a leading shock and a lagging shock by which the corresponding local vortex flows are accelerated and decelerated, respectively: the vortex flow swept by the leading shock is locally expanded and the one behind the lagging shock is locally compressed. As the leading shock escapes the vortex in the order of microseconds, the expanded flow region is quickly changed to a compression region due to the implosion effect. An induced shock is developed here and propagated against the vortex flow. This happens for a strong vortex because the tangential flow velocity of the vortex core is high enough to make the induced-shock wave speed supersonic relative to the vortex flow. For a weak shock, the vortex is basically subsonic and the induced shock wave is absent. For a vortex of intermediate strength, an induced shock wave is developed in the supersonic region but dissipated prematurely in the subsonic region. We have expounded these three shock-vortex interaction patterns that depend on the vortex flow regime using a third-order ENO method and numerical shadowgraphs.

• 한국신재생에너지학회:학술대회논문집
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• 한국신재생에너지학회 2007년도 춘계학술대회
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• pp.414-419
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• 2007

This paper describes the prediction of aerodynamic performance and wake of HAWT in normal and yawed flow operation using potential based methods. In order to analyze aerodynamic performance of wind turbine WINFAS program is used, which is based on VLM(Vortex Lattice Method) and CVC(Constant vorticity contour) Free wake model. Some problems of CVC vortex filament method are investigated arid to improve these problems vortex ring wake are introduced in behalf of CVC vortex filament. The prediction results using the vortex lattice wake are compared to experimental data.

• 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.

• International Journal of Aeronautical and Space Sciences
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• 제6권2호
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• pp.84-96
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• 2005

Helical tip vortex is known as stable vortex structure, however the specific frequency component of far wake perturbation induces the vortex pairing in hover and axial flight. It is expected that the tip vortex pairing phenomena may happen in transition flight and very low advance ratio flight so that inflow may be most nonuniform in the low advance ratio flight. The objectives of this paper are that a tip-vortex instability during the transition from hover into very low advance ratio forward flight is numerically predicted to understand a physics by using a time-marching free-wake method. To achieve the objectives, numerical method is firstly validated in typical axial and forward flights cases. Present scheme with trim routine can predict airloads and inflow distribution of forward flight with good accuracy. Then, the transition flight condition is calculated. The rotor used in this wake calculation is a small-scale AH-1G model. By using a tip-vortex trajectory tracking method, the tip-vortex pairing process are clearly observed in transient flight($\mu$=0.03) and disappears at a slightly higher advance ratio($\mu$=0.05). According to the steady flight simulation at $\mu$=0.03, it is confirmed the tip-vortex pairing process is continued in the rear part of rotor disk and not occurs in the front part. Time averaged inflow in this case is predicted as smooth distribution.

• 융복합기술연구소 논문집
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• 제4권1호
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• pp.37-41
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• 2014

For the analysis of lifting surface at high angle of attack, a Nonlinear Vortex Lattice Method(NLVLM) was used. The NLVLM is intented to compute the interactions between lifting surfaces and separated vertical flow. The lifting surfaces are represented by a lattice of discrete vortex rings. And wakes are represented by families of non-lintersecting, semi-infinite vortex line segments. The image method also used to analyze the ground effect. It is found that vortex lines separated from lifting surfaces represent the separated flows successfully. Although the present method is applied for the rectangular wing and delta wing, extensions can be possible for the arbitrary lifting surfaces. The Present results show good agreement with experimental data.

• 대한기계학회논문집
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• 제14권5호
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• pp.1264-1271
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• 1990

본 연구에서는 회전 깃(rotor blade)을 폭 방향과 시위방향으로 많은 평면 페 널(panel)들로 나누어 이에 말굽쇠 형 화류(horseshoe vortex)를 분포시키는 양력면 (lifting surface)으로 대치하고 후류는 깃상의 순환(circulation)분포에 의해 그 크 기가 결정되는 와도(vorticity)를 와류격자로 대치하는 와류격자법(Vortex Lattice Method`VLM)을 사용하여 HAWT의 공기역학적 성능 예측을 시도하였다. 그리고 후류의 형상은 근 후류(near wake)와 원후류(far wake)로 나누어 근 후류는 깃의 후연(trail- ing edge)에서의 속도를 갖고 와선(vortex line)이 움직이게 하여 결정하였고 원 후류 는 반무한대 원형화류 실린더(semi-infinite circular vortex cylinder)로 취급하여 결정하였다.

• 한국항공우주학회지
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• 제36권11호
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• pp.1039-1048
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• 2008

본 논문에서는 새로운 비선형 와류격자법 계산 과정이 제안된다. 기존의 계산 과정은 자유와의 형태 계산을 위해 내부 반복계산 및 하향이완법을 포함한다. 하지만 본 논문에서는 유사 정상 개념에 기초한 새로운 수식을 제안하여 자유와의 형태를 계산함으로써, 계산 과정에서 내부 반복계산 및 하향이완법을 생략한다. 또한 반복계산이 진행됨에 따라 각 분절에 유도되는 유속도를 적절히 평균해 줌으로써 알고리듬의 수치적 안정성을 향상시킨다. 그리고 낮은 종횡비 날개에 대한 수치실험을 수행하여 분절의 길이, 와류중심반경, 후류영역 계산범위 등과 같은 중요 인자들의 적절한 기준을 경험적으로 결정한다.

• 항공우주시스템공학회지
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• 제10권1호
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• pp.1-7
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• 2016

During flight of the aircraft, the vortex merging phenomenon appears under the certain condition between co-rotating vortices which were generated at the wing tip and lifting-surface. And then these merged vortices at both sides show counter-rotating pattern to affect on the downstream of the aircraft. In this paper, the numerical simulations are conducted assuming this phenomenon in two-dimensional co-rotating or counter-rotating vortices pairs. Two-dimensional incompressible Navier-Stokes equations were converted into Vorticity-Streamfunction form and the Galerkin spectral method was adopted. The third order Runge-Kutta method was used for time integration. The effects on the vortex merger and degree of vortex merger were investigated according to time, Reynolds number, and changes in the distance between two vortices.

• 대한조선학회논문집
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• 제46권3호
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• pp.249-258
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• 2009

DVM (Discrete Vortex Method) is a numerical scheme that handles discrete vortex particles to express continuous vorticity field. This scheme is proper to VIV (Vortex Induced Vibration) analysis because there is no need to generate field grids and VIV is caused by separated vorticity from the body. When DVM is applied to VIV analysis, there are some applicable schemes such as using vortex blobs, integral method for computing induced velocity, etc. In this study, the influences of these schemes are investigated and the practical scheme that is appropriate for VIV analysis is proposed.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2004년도 춘계 학술대회논문집
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• pp.161-165
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• 2004

In the vortex particle method based on the vorticity-velocity formulation for solving the Wavier-Stokes equations, the unsteady, incompressible, viscous laminar flow over a NACA 0012 foil is simulated. By applying an operator-splitting method, the 'convection' and 'diffusion' equations are solved sequentially at each time step. The convection equation is solved using the vortex particle method, and the diffusion equation using the particle strength exchange(PSE) scheme which is modified to avoid a spurious vorticity flux. The scheme is improved for variety body shape using one image layer scheme. For a validation of the present method, we illustrate the early development of the viscous flow about an impulsively started NACA 0012 foil for Reynolds number 550.