• Journal of Ship and Ocean Technology
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• 제8권4호
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• pp.10-16
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• 2004

A response of a swept wing boundary layer to a single free-stream stationary axial vortex of a limited spanwise extent is considered as an example of typical problems that one can find in laminar-turbulent transition research and control. The response is dominated by streamwise velocity perturbations that grow quasi-exponentially downstream. It is shown that the formation of the boundary layer disturbance occurs for the most part close to the leading edge. The disturbance represents itself a wave packet consisted of the waves with characteristics specific for cross-flow instability. However, an admixture of growing disturbances whose origin can be attributed to transient effects and to a distributed receptivity mechanism is also identified.

• 한국가스학회지
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• 제6권1호
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• pp.81-85
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• 2002

탱크와 연결된 배관에서 원하지 않은 사고로 인해 액체 위험물질의 누출이 발생할 경우 천이영역에서의 누출속도 계산방법을 제시하였다. 배관에서의 액누출에 관한 누출속도는 층류와 난류영역에서 Crowl and Louvar 등이 제시한 모델식을 이용하여 프로그램 또는 직접계산에 의해 이루어지고 있으나, 천이영역에 대한 모델식은 없었다. 따라서 본 논문에서는 Lap-Mou Tam 등이 실험한 천이영역에서 레이놀즈수에 따른 마찰계수 실험값을 이용하여 천이영역에 대한 누출속도 값을 계산하였고 이 값을 층류와 난류에 관한 모델식을 사용한 값과의 비교를 통해 천이영역에서 일반적으로 사용할 수 있는 모델식으로 난류에 관한 모델식으로 계산한 값에 안전율 $30\%$를 추가한 값을 위험평가에 사용할 수 있음을 보였다.

• 한국항공우주학회지
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• 제45권5호
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• pp.367-375
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• 2017

본 연구에서는 초음속 영역에서의 해머헤드형 노즈 페어링을 포함하고 있는 발사체 선두부에 대한 RANS 전산해석을 수행하였다. 층류, 완전 난류, 천이 모델을 이용한 2차원 축대칭 해석을 수행하여 실험 결과와 비교하였다. 레이놀즈수의 변화에 따라서 다른 유동현상이 나타남을 확인하였다. 높은 레이놀즈수에서는 경계층이 난류가 되어 발사체 표면에서 박리가 되지 않는다. 낮은 레이놀즈수 조건에서는 해머헤드형 노즈 페어링의 팽창-압축 모서리에서 경계층의 박리와 재부착으로 층류 박리 거품이 만들어진다. 받음각이 있는 3차원 계산에서 층류 박리 거품으로 발생되는 와류 구조를 확인할 수 있었다. 레이놀즈수에 따른 박리 거품을 예측하기 위해서 난류 천이를 고려해야 함을 확인할 수 있었다.

• 대한기계학회논문집B
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• 제22권9호
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• pp.1335-1348
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• 1998

Flow characteristics in transitional boundary layers on a flat plate were experimentally investigated under three different freestream conditions i. e. uniform flow with 0.1 % and 3.7% freestream turbulent intensity and cylinder-wake with 3.7% maximum turbulent intensity. Instantaneous streamwise velocities in laminar, transitional and turbulent boundary layers were measured by I-type hot-wire probe. For estimation of wall shear stresses on the flat plate, measured mean velocities near the wall were applied to the principle of Computational Preston Tube Method (CPM). Distributions of skin friction coefficients were reasonably predicted in all developed boundary layers. Intermittency profiles, which were estimated using Conditional Sampling Technique in transitional boundary layers, were also consistent with previously published data. It was predicted that the incoming turbulent intensity had more influence on transition onset point and transition process than freestream turbulent intensity existed just over the transition region. It was also confirmed that non-turbulent and turbulent profiles in transitional boundary layers could not be simply treated as Blasius and fully turbulent profiles.

• 한국안전학회지
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• 제33권1호
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• pp.7-15
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• 2018

The friction factors according to the flow regimes in helical coil tubes depend on the coil diameter, the tube diameter, and the coil pitch. In previous studies, correlations for the laminar flow regime in helical coil tubes have been proposed. However, studies on the transition flow regime and the turbulent flow regime are insufficient and further researches are necessary. In this study, characteristics of the friction factors for the laminar, transition and turbulent flow regimes in helical coil tubes were experimentally investigated. The helical coil tubes used in the experiments were made of copper. The curvature ratios of the helical coil tubes, which means the ratio of helical coil diameter to inner diameter of the helical coil tube are 24.5 and 90.9. Experiments were carried out in the range of $529{\leq}Re{\leq}39,406$ to observe the flows from the laminar to the turbulent regime. The friction factors were obtained by measuring the differential pressures according to the flow rates in the helical coil tubes while varying the curvature ratios of the helical coil tubes. Experimental data show that the friction factors for the helical coil tube with 24.5 in the curvature ratio of the helical coil tube were larger than those in the straight tube in all flow regimes. As the curvature ratio of the helical coil tube increases, the friction factor in turbulent flow regime tends to be equal to that of the straight tube. In addition, it was confirmed that the transition flow regimes in the helical coil tubes were much wider than those in the straight tube, also the critical Reynolds numbers were larger than those in the straight tube. The results obtained in this experimental study can be used as basic data for studies on the water hammer phenomenon in helical coil tubes.

• International Journal of Naval Architecture and Ocean Engineering
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• 제13권1호
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• pp.236-245
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• 2021

In this study, direct numerical and large eddy simulations of transitional flows around studs were conducted to investigate the effectiveness of turbulence stimulators at very low speeds for the minimum propulsion power condition of four knots. For simplicity, the studs were assumed to be installed on a flat plate, while the wake was observed up to 0.23 m downstream behind the second stud. For applicability to a model ship, we also studied the flow characteristics behind the first and second studs installed on a curved plate, which was designed to describe the geometry of a bulbous bow. A laminar-to-turbulent transition was observed in the wake at Re_D ≥ 921 (U_∞≥0.290 m/s), and the wall shear stress at Re_D = 1162 (U_∞ = 0.366 m/s) in the second wake was similar to that of the fully developed turbulent boundary layer after a laminar-to-turbulent transition in the first wake. At Re_D = 581 (U_∞ = 0.183 m/s), no turbulence was stimulated in the wake behind the first and second studs on the flat plate, while a cluster of vortical structures was observed in the first wake over the curved plate. However, a cluster of vortical structures was revealed to be generated by the reattachment process of the separated shear layer, which was disturbed by the first stud rather than directly initiated by the first stud. It was quite different from a typical process of transition, which was observed at relatively high Re_D that the spanwise scope of the turbulent vortical structures expanded gradually as it went downstream.

• 대한기계학회논문집B
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• 제26권5호
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• pp.685-694
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• 2002

Effects of wake-passing orientation and frequency on the wake-induced boundary layer transition on a NACA0012 airfoil are investigated. The wakes are generated by rotating cylinders clockwise (CW) and counterclockwise (CCW) around the airfoil. Time- and phase-averaged streamwise mean velocities and turbulent fluctuations are measured with a single hot-wire probe. Wall skin frictions are estimated by the Computational Preston Tube Method (CPM). The pressure distribution on the airfoil is different according to the wake-passing orientation and frequency. Turbulent patches are generated in the laminar boundary layer due to the passing wake and the boundary layer becomes temporarily transitional. The transition process is significantly affected by the pressure gradient and the turbulent patches. For the receding wake, the turbulent patches propagate more rapidly than those for the approaching wake because adverse pressure gradient becomes larger. As the frequency increases, onset location of transition moles upstream and the boundary layer near the trailing edge becomes more transitional.

• 대한조선학회논문집
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• 제58권1호
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• pp.1-9
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• 2021

In the present study, the model-scale Propeller Open Water (POW) tests for the propeller of 176K bulk carrier and 8600TEU container ship were conducted through Computational Fluid Dynamics (CFD) simulation. In order to solve the incompressible viscous flow field, the Reynolds-averaged Navier-Stokes (RaNS) equations were employed as the governing equations. The γ-Reθ(gamma-Re-theta) transition model combined with the SST k-ωturbulence model was introduced to describe the laminar-turbulence transition considering the low Reynolds number of model-scale. Firstly, the flow simulation developing over a flat plate was performed to verify the transition modeling, in which the wall shear stresses were compared with experiments and other numerical results. Then, to investigate the effect of the model, the CFD simulation for the POW test was performed and the simulated propeller performance was validated through comparison with the experiment conducted at Korea Research Institute of Ships & Ocean Engineering (KRISO).

• 공업화학
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• 제16권5호
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• pp.698-704
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• 2005

구형교반조 및 원통교반조에서 paddle 임펠러의 교반소요동력을 넓은 범위의 레이놀즈수 영역에서 측정하였다. 구형교반조는 교반조 높이가 직경과 같고, 구형교반조의 체적과 같은 원통교반조의 겉보기 직경을 이용하여 구형교반조 및 원통교반조 모두에 적용할 수 있는 교반소요동력 상관식을 구했다. 이 상관식은 Nagata 등 및 Hixson 등의 실험결과에도 양호하게 상관되었다. 또한 임계레이놀즈수는 본 상관식에서 얻은 층류영역에서 난류영역으로의 전이에 관한 계수 $C_{tr}$에 잘 상관되었다.

• 한국항공우주학회지
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• 제44권6호
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• pp.477-483
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• 2016

본 연구는 Particle Image Velocimetry(PIV) 기법을 이용하여 마하수 2.96의 평판에 대해 층류, 천이, 난류 경계층의 속도 분포를 측정하였다. Schlieren 가시화 기법과 PIV 기법을 이용하여 앞전에서 발생한 경사 충격파가 평판 위의 유동장에 영향을 주는지 확인하였다. 층류 경계층의 경우, 실험에서 측정한 속도 분포가 압축성 Blasius 속도 분포를 만족하였다. 천이 경계층의 속도 분포는 벽면 부근부터 이론적인 난류 속도 분포로 변했으며, Re = $1.41{\times}10^6$에서 천이가 시작되었다. 난류 경계층 영역에서는 압축성 효과를 고려한 Van Driest 변환 속도가 비압축성 로그 법칙을 만족하였다. 또한 로그 구간이 끝나는 위치($y/{\delta}{\approx}0.28$)가 비압축성 난류 경계층($y/{\delta}{\approx}0.2$)에 비해 벽면에서 더 멀어진 것을 확인하였다.