• 한국항공우주학회지
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• 제45권3호
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• pp.233-240
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• 2017

본 연구에서는 전산유체역학의 특징에 대한 이해를 위해 천음속 날개-동체 주위의 유동장을 In-house 전산유체 코드로 해석하여 시험 결과와 비교하였다. 날개는 RAE 101 익형 단면을 가진 RAE Wing 'A'이며 동체는 축대칭 형상이다. In-house 코드는 비정렬 격자 기반의 압축성 Euler/Navier-Stokes 해석 코드이다. 격자에 대한 의존도, 난류 모형, 공간차분 기법, 점성/비점성의 영향을 시험 결과와 비교하여 살펴보았다. 난류 모형은 $k-{\omega}$ 모형, Spalart-Allmaras 모형, $k-{\omega}$ SST을 적용하였고, 공간차분 기법은 Jameson의 인공 점성를 도입한 중앙 차분 기법과 Roe의 풍상 차분 기법을 적용하였다. 대체적으로 시험 결과를 잘 예측하였으나, 압력분포 및 충격파의 위치가 난류 모형 및 공간 차분 기법에 따라 조금씩 다르게 예측되었으며, 정확한 충격파 위치를 예측하기 위해서는 난류 점성 효과가 고려되어야 함을 알 수 있다.

• 한국해안·해양공학회논문집
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• 제32권1호
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• pp.55-68
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• 2020

너울이 우세한 온화한 해양환경에서 출현하는 beach cusp에서의 경계층 streaming 수리특성을 살펴보기 위해 edge waves의 천수 과정을 수치 모의하였다. Beach cusp을 유지하는 것으로 알려진 synchronous edge waves는 같은 주기와 파고를 지니는 두 개의 Cnoidal wave가 전면해역에서 비스듬히 조우 되도록 조파하여 재현하였다. Beach cusp의 진폭 A_B과 파장 L_B은 맹방 해변에서 수행된 관측결과를 토대로 각각 1.25 m, 18 m로 선정하였다. 모의결과 천수 각 단계에서 예외 없이 경계층 streaming을 관측할 수 있었으며 최대 경계층 streaming은 사주 정점에서 발생하였다. 주기가 가장 짧은 RUN 1의 경우 그 세기는 약 0.32 m/s 내외에 분포하며 이러한 수치는 free stream 유속 u_∞ 진폭의 두 배에 달하는 것으로 wave Reynolds 응력에 기반한 Longuet-Higgins(1957)의 해석 해와는 상당한 차이를 보였다. 수치 모의과정에서 온화한 해양환경에서 해빈이 복원되는 과정을 특정할 수 있었으며 이 과정을 정리하면 다음과 같다: 너울로 구성된 파랑 무리에서 성분 파랑 간의 공진성 상호작용으로 생성된 외 중력파가 쇄파선 인근에 도달하는 경우 중력으로 인한 가속이 더해진 Phase II 파랑 궤도 운동으로 수면 가까이 상승한 많은 모래가 쇄파 시 발생하는 파 마루로부터 시작된 up-rush에 의해 전 빈 정점 가까이 이동하며 이 과정에서 발생하는 침투로 인해 퇴적되는 것으로 모의 되었다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 1998년도 춘계 학술대회논문집
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• pp.117-122
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• 1998

A numerical study is carried out to investigate the transient process of combustion phenomena associated with hypersonic propulsion devices. Reynolds averaged Navier-Stokes equations for reactive flows are used as governing equations with a detailed chemistry mechanism of hydrogen-air mixture and two-equation SST turbulence modeling. The governing equations are discretized by a high order accurate upwind scheme and solved in a fully coupled manner with a fully implicit time accurate method. At first, oscillating shock-induced combustion is analyzed and the comparison with experimental result gives the validity of present computational modeling. Secondly, the model ram accelerator experiment was simulated and the results show the detailed transient combustion mechanisms. Thirdly, the evolution of oblique detonation wave is simulated and the result shows transient and final steady state behavior at off-stability condition. Finally, shock wave/boundary layer interaction in combustible mixture is studied and the criterion of boundary layer flame and oblique detonation wave is identified.

• 대한기계학회논문집B
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• 제26권3호
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• pp.375-383
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• 2002

The flowfield of transverse jet in a supersonic air stream subjected to shock wave turbulent boundary layer interactions is simulated numerically by Generalized Taylor Galerkin(GTG) finite element methods. Effects of turbulence are taken into account with a two-equation (k-$\varepsilon$) model with a compressibility correction. Injection pressures and slot widths are varied in the present study. Pressure, separation extents, and penetration heights are compared with experimental data. Favorable comparisons with experimental measurements are demonstrated.

• 한국신재생에너지학회:학술대회논문집
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• 한국신재생에너지학회 2011년도 추계학술대회 초록집
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• pp.38.1-38.1
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• 2011

This study investigates the effects of Pierson-Moskowitz, Jonswap spectrum that are typical irregular wave spectrums for wind turbine system with jacket support structure. Also various offshore environmental parameters based on korean local condition were used in our study. The loads acting on the system was considered by referring to the Design Load Case from IEC guide line. And improved von Karman model was used as a turbulence model. As a result, various significant wave height and peak spectral period cause noticeable difference of extreme and fatigue loads prediction.

• Journal of Ship and Ocean Technology
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• 제5권1호
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• pp.38-54
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• 2001

A finite difference method for calculating turbulent flow and surface wave fields around a ship model is evaluated through the comparison with the experimental data of a Series 60 $C_B$=0.6 ship model. The method solves the Reynolds-averaged Navior-Stokes Equations using the non-staggered grid system, the four-stage Runge-Kutta scheme for the temporal integration of governing equations and the Bladwin-Lomax model for the turbulence closure. The free surface waves are captured by solving the equation of the kinematic free-surface condition using the Lax-Wendroff scheme and free-surface conforming grids are generated at each time step so that one of the grid surfaces coincides always with the free surface. The computational results show an overall close agreement with the experimental data and verify that the present method can simulate well the turbulent boundary layers and wakes as well as the free-surface waves.

• 대한기계학회논문집
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• 제19권6호
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• pp.1510-1517
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• 1995

A theoretical method is described to simulate the propagation of turbulent premixed flames in a closed vessel. The objective is to develop and test an efficient technique to predict the propagation speed of flame as well as the geometric structure of the flame surfaces. Flame is advected by the statistically generated turbulent flow field and propagates as a wave by solving twodimensional Hamilton-Jacobi equation. In the simulation of the unburned gas flow field, following turbulence properties were satisfied: mean velocity field, turbulence intensities, spatial and temporal correlations of velocity fluctuations. It is assumed that these properties are not affected by the expansion of the burned gas region. Predictions were compared with existing experimental data for flames propagating in a closed vessel charged with hydrogen/air mixture with various turbulence intensities and Reynolds numbers. Comparisons were made in flame radius growth rate, rms flame radius fluctuations, and average perimeter and fractal dimensions of the flame boundaries. Two dimensional time dependent simulation resulted in correct trends of the measured flame data. The reasonable behavior and high efficiency proves the usefulness of this method in difficult problems of flame propagation such as in internal combustion engines.

• 한국전산유체공학회지
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• 제4권2호
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• pp.57-66
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• 1999

Numerical Analysis has been done for the supersonic off-design jet flow due to the pressure difference between the jet and the ambient fluid. The difference of pressure generates an oblique shock or an expansion wave at the nozzle exit. The waves reflect repeatedly on the center axis and the sonic surface in the shear layer. The pressure difference is resolved across these reflected waves. In this paper, the axi-symmetric Navier-Stokes equation has been used with the κ-ε turbulence model. The second order TVD scheme with flux limiters, based on the flux vector split with the smooth eigenvalue split, has been used to capture internal shocks and other discontinuities. Numerical calculations have been done to analyze the off-design jet flow due to the pressure difference. The variation of pressure along the flow axis is compared with an experimental result and other numerical result. The characteristics of the interaction between the shock cell and the turbulence mixing layer have been analyzed.

• 한국해양공학회지
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• 제22권3호
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• pp.24-33
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• 2008

In this study, flow and creation and dissipation of vorticity around rectangular floating breakwater is investigated both experimentally and numerically. The PIV system(Particle image velocimetry) is employed to obtain the velocity field in the vorticity of rectangular structure. The numerical model, combined with ${\kappa}-{\varepsilon}$ turbulence model and the VOF method based on RANS equation, is used to analyze the turbulence structure. In the results of this study, the vorticity is found around conner of rectangular structure at all time domain, and creation and dissipation of vorticity are closely related to wave period. Separation points of phase of vortex due to flow separation for longer period waves are faster then for shorter period waves.

• 한국추진공학회지
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• 제6권2호
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• pp.75-84
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• 2002

고체 추진 로켓 내부 연소실의 비정상 유동을 수치적으로 해석하였다. 완전 보존식을 이용하여 2 차원 축-대칭 연소실 안의 연소 불안정을 해석하기 위한 수치 기법을 구성하였는데 비정상 유동을 해석하기 위한 수정된 $\kappa$-$\varepsilon$ 난류 모델이 사용되었다. 이산화한 지배 방정식은 연관된 경계 조건을 포함하여 dual time-stepping 방법으로 시적분 하였다. 정상 상태의 계산을 기반으로 연소실 내의 천이 압력파의 비정상 상태를 수치적으로 모사하기 위하여 압력 펄스 및 압력 변동을 연소실 상단에 부과하였다. 로켓 모터 연소실 내의 다양한 정상 상태 및 비정상 상태의 특성을 계산 및 해석하였다.