• Proceedings of the Korean Vacuum Society Conference
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• 2014.02a
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• pp.240.1-240.1
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• 2014

대기압 플라즈마 제트 장치에 주입되는 기체의 유량 변화에 따른 방전 특성을 유체역학적으로 해석하였다. 장치에 주입되는 기체의 유량 변화는 레이놀즈수에 의한 유체 흐름의 상태 변화와 베르누이 정리에 의한 압력 변화를 동반한다. 유리관에 주입되는 기체의 레이놀즈수가 Re<2000이면 층류이며 Re>4000이면 난류, 2000

• Journal of Advanced Marine Engineering and Technology
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• v.34 no.1
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• pp.76-83
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• 2010

The Characteristics of the flow field through cylinders with in-line and staggered arrangements were calculated by vortex method. Vortex distributions and velocity profiles around the cylinders with in-line and staggered arrangements were simulated at the pitch ratio of Pt/D=1.25~2.0 and Reynolds number of Re=$4.0{\times}10^1{\sim}4.0{\times}10^4$. As the results the vortices of clockwise at the upper separation point cylinder and the vortices of anticlockwise at the lower separation point of each cylinder were generated at both in-line and staggered arrangements. The generation of the reverse flow in the rear region of the cylinders was caused by the pitch ratio and Reynolds number, the boundary region was at the pitch ratio of Pt/D=1.5 and Reynolds number of Re=$4.0{\times}10^2{\sim}4.0{\times}10^3$ in case of in-line arrangement and was at the pitch ratio of Pt/D=1.4 and Reynolds number of Re=$4.0{\times}10^1{\sim}4.0{\times}10^2$ in case of staggered arrangement.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.10
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• pp.16-23
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• 2006

A study on the boundary layer behavior of an NACA 0012 airfoil at low Reynolds numbers was investigated in order to gain knowledge of a boundary layer that might be employed in a turbine blade and MAVs. A hot-wire anemometer was used to measure the boundary layer of an NACA 0012 airfoil at static angles of attack ${\alpha}$=$0^{\circ}$, $3^{\circ}$, and $6^{\circ}$, and Reynolds Numbers Re=$2.3{\times}10^4$, $3.3{\times}10^4$, and $4.8{\times}10^4$. The results of this study show that the laminar boundary layer on the airfoil surface is attached to the surface at ${\alpha}$=$0^{\circ}$, and the laminar separation of the boundary layer on the airfoil surface occurs at ${\alpha}$=$3^{\circ}$. Furthermore, the reattachment of the boundary layer in the present study occurs for the cases of Re=$3.3{\times}10^4$ and Re=$4.8{\times}10^4$at ${\alpha}$=$6^{\circ}$.

• Journal of the Korean Society of Marine Environment & Safety
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• v.15 no.2
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• pp.151-156
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• 2009

This experimental study investigated in to the flow characteristics around staggered cooling tube arrays of fan coil unit for ship. A particle image velocimetry technique was employed to obtain detailed measurements at inlet-velocity-based Reynolds numbers of $Re=1.5{\times}10^3{\sim}Re=2.5{\times}10^3$. As for the results, the flow evolves rapidly and becomes spatially periodic in the streamwise direction after a relatively short distance. The flow exhibits strong Reynolds number dependence in developing region but no significant Reynolds number effects are observed in spatially periodic region.

• Journal of computational fluids engineering
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• v.6 no.4
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• pp.35-42
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• 2001

In this study, numerical calculations are carried out in order to evaluate the performance of low-Re Reynolds stress model based on SSG model for a swirling turbulent flow in a pipe. The results are compared with those of k-ε model, GL model and the experimental data. The results show that low-Re Reynolds stress model and GL model give better results than k-ε model. In the region near the wall, low-Re Reynolds stress model improves the predictions. However, there is no large difference between the predictions with two Reynolds stress models.

• Proceeding of EDISON Challenge
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• 2012.04a
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• pp.29-32
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• 2012

변장비의 변화가 사각실린더에 작용하는 유체력에 미치는 영향을 알기 위해 EDISON_열유체를 사용하여 수치해석을 하였다. 낮은 레이놀즈수 영역($100{\leq}Re{\leq}200$)에서 사각실린더의 변장비(W/H)를 0.5, 0.75, 1, 2로 변화시키며 해석을 수행하였고, 레이놀즈수와 변장비에 따른 스트로할수(St), 항력계수($C_D$), 양력계수($C_L$)를 비교하였다. 본 논문에서는 레이놀즈수와 실린더의 변장비가 스트로할수, 항력계수, 양력계수에 미치는 영향을 알아보는 데 중점을 두었다. 해석결과 레이놀즈수가 증가하고 변장비가 감소할수록 스트로할수, 항력계수, 양력계수가 증가하는 것을 확인하였다. 본 논문을 통해서 레이놀즈수와 사각실린더의 변장비가 사각실린더에 작용하는 유체력에 영향을 미친다는 것을 알 수 있었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.2
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• pp.137-145
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• 2008

An experimental study was performed in order to investigate the influence of Reynolds number on the drag coefficient variations of an oscillating airfoil. A NACA 0012 airfoil was sinusoidally pitched at the quarter chord point with an oscillating amplitude of ${\pm}6^{\circ}$. The free-stream velocities were 1.98, 2.83 and 4.03 m/s and the corresponding chord Reynolds numbers were $2.3{\times}10^4$, $3.3{\times}10^4$ and $4.8{\times}10^4$, respectively. The drag coefficient was calculated from the ensemble average velocity measured by an X-type hot-wire probe(X-type, 55R51) in the near-wakes region. In the case of Re=$2.3{\times}10^4$, variation of drag coefficient shows a negative damping (counter-clockwise variation), which implies an unstable state which could be excited by aerodynamic force, whereas the drag coefficient represents the positive damping (clockwise variation) as the Reynolds number increases from Re=$3.3{\times}10^4$ to $4.8{\times}10^4$. Hence, the drag coefficient variations show significant differences between Re=$2.3{\times}10^4$ and $4.8{\times}10^4$이다.

• Journal of Advanced Marine Engineering and Technology
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• v.33 no.8
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• pp.1180-1186
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• 2009

This experimental study is about the flow characteristics according to existence and nonexistence of the control rod and location in the flow field where it has the Inclined rear walls in the open cavity. By using the visualization of flow and particle image velocimetry (PIV), we performed about a change and speed of the Reynolds number. Our objective was what part of the control rod gives less effects to the characteristics of flow and how the shear mixing layer moves at what critical point of the Reynolds number. As a result, we differed the location of control rod. So finally, L/H=0.2 was discovered to give less effects to the cavity. The flow of backside of vortex faces the upper side. And we found that this phenomenon shows up more clear when the number of Reynolds increases. This is because of the flow of vortex causes by the condition of y/H=1.0. This phenomenon gets more clear with increasing of number of Reynolds, and critical point of the Reynolds number was $Re=1.0{\times}10^4$ around. If control rod is L/H=0.1, depending on the number of Reynolds ($Re=6.0{\times}10^3$, $Re=8.0{\times}10^3$, $Re=1.0{\times}10^4$, $Re=1.2{\times}10^4$), doubled vortex shows up. As the shear mixing layer of the upper side of cavity increases, the speed of the lower side was very stable.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.40 no.7
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• pp.435-440
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• 2016

Effects of the increase rate of Reynold number on near-wall turbulent structures are investigated by performing direct numerical simulations of transient turbulent channel flows. The simulations were started with the fully-developed turbulent channel flow at $Re_{\tau}=180$, then temporal accelerations were applied. During the acceleration, the Reynolds number, based on the channel width and the bulk mean velocity, increased almost linearly from 5600 to 13600. To elucidate the effects of flow acceleration rates on near-wall turbulence, a wide range of durations for acceleration were selected. Various turbulent statistics and instantaneous flow fields revealed that the rapid increase of flow rate invoked bypass-transition like phenomena in the transient flow. By contrast, the flow evolved progressively and the bypass transition did not clearly occur during mild flow acceleration. The present study suggests that the transition to the new turbulent regime in transient channel flow is mainly affected by the flow acceleration rate, not by the ratio of the final and initial Reynolds numbers.

• 한국전산유체공학회:학술대회논문집
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• 2000.10a
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• pp.135-140
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• 2000

Numerical calculations are carried out in order to evaluate the performance of low-Re Reynolds stress model based on SSG model for a swirling turbulent flow in a pipe. The results are compared with those of $\kappa-\epsilon$ model and GL model, and the experimental data. The finite volume method is used for the discretization, and the power-law scheme is employed as a numerical scheme. The SIMPLE algorithm is used for velocity-Pressure correction in the governing equations.