• 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 ${\alpha}$=$6^{\circ}$.

• Proceedings of the Membrane Society of Korea Conference
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• 1994.10a
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• pp.77-79
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• 1994

폐수와 하수처리에서 양질의 재생수를 얻기위하여 고분자막을 이용한 폐수재활용에서 나타나는 공정상 문제점을 고찰하였다. 본 연구에서 사용한 폐수는 처탑공장의 폐수로서 RO막을 이용한 폐수의 재이용공정개발을 목표로하고 있으며, pilot실험을 토대로 폐수의 적용성 검토가 행하여졌다. 사용된 막의 종류는 중공사막형의 막으로서 막내의 층류 흐름의 응용은 투석막, 기체분리, 중금속의 추출등 상당한 관심속에 있다. 여기서 중공사막과 같은 관(Cynlindrical)형의 막 구조에서 물질과 에너지 이동현상은 막분리공정을 이해하는 중요한 물리적고찰로서 막투과도를 높힐수 있을 뿐만 아니라 운전온도에 의해 중공사막 RO막내의 유량변화에 주요한 변수가 될 수 있다.

• Proceedings of the KSR Conference
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• 2009.05a
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• pp.1680-1686
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• 2009

Flow characteristics of a differential pressure flow meters which have a shape of triangular separate bar (TSB) was investigated according to machining conditions in pressure tapping holes. Size of pressure tapping holes is machined with either 1.0 mm or 1.5 mm in diameter. Also, number of pressure tapping holes are drilled either 9 or 17. The mass flow rate of the TSB flow meters are calibrated with a laminar flow meter by connecting them in line. The mass flow rate in the TSB flow meters are plotted with a non-dimensional parameter H which includes the gas temperature, exhaust gas pressure and differential pressure at the flow meters, and atmospheric pressure. An empirical correlation between the mass flow rate at the TSB flow meter and the non-dimensional parameter H was obtained. The empirical correlation showed highly linear relationship between the mass flow rate and the non-dimensional parameter H. The hole size of the pressure tapping holes has a bigger effect on the flow rate than the number of the tapping holes.

• Proceedings of the Korean Nuclear Society Conference
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• 1998.05a
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• pp.603-608
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• 1998

유체내의 물체 주위에서 유동박리로 인해 생성되는 와류쉐딩은 열전달이나 물질전달을 촉진시키는 이점이 있으나, 항력을 증가시키거나 유동 및 온도의 요동에 의해 구조물을 손상시키는 단점이 있다. 특히 물체와 주위 유동 사이에 공진이 일어나면 항력값이 증가하면서 항력과 양력의 진폭이 급격히 증가하여 물체에 심각한 손상을 초래할 수 있다. 본 연구에서는 레이놀즈수 200 이하의 층류유동에서 공진시 물체 주위의 유동현상과 이로 인한 양력과 항력의 변화들을 수치해석방법을 통하여 분석하였다 수치해석은 일반좌표계에서 유한체적법을 적용하여 Navier-Stokes 방정식을 차분화하였다. 이때 방정식의 종속변수로는 공변속도를 채택하였으며, 이산화된 방정식은 분리단계법을 이용하여 수치해를 구하였다. 입구유속의 강제진동에 의한 사각실린더 주위의 와류쉐딩시 공진이 발생하는 강제진동수의 범위는 원통실린더의 경우와 유사하였으나 상대적으로 폭이 더 좁았다 그리고 공진이 발생하는 강제진동수의 범위는 진폭이 증가할수록 증가하였다. 쉐딩 진동수가 일정하면서 입구유속의 진폭이 증가하면 이에 비례하여 실린더 주위의 유속이 상대적으로 증가하게 되어 와도가 강해지면서 입추유속 진폭에 비례하여 항력의 평균값 뿐 아니라 항력과 양력의 진폭도 증가하였다. 그리고 실린더 뒷면의 와류 생성영역은 진폭에 비례하여 감소하였다. 진폭의 변화에 따라 상변화가 서로 상이한 것은 실린더 뒤쪽의 와류들이 상하면의 합력차이를 변화시켰고 이것이 진폭변화에 따라 상변화를 상이하게 나타나게 한 원인으로 진폭이 클수록 실린더 뒤쪽에서 압력변화가 심하게 변하면서 실린더 앞쪽까지 더 많은 영향을 미쳤기 때문이다.선원의 사용자에게 제공되는 최종방사능을 평가하는데 유용하게 사용될 수 있다.r의 분포를 보였다.cting the effect of earthquake on structures. This paper is based on the presented paper at the Bertero Symposium held in January 31an4 February 1 at Berkeley, California, USA which was entitled "Needs to Evaluate Real Seismic Performance of Buildings-Lessons from 1995 Hyogoken-Nambu Earthquake-". The lessons for buildings from the damage due to the Hyogoken-Nambu Earthquake are necessity to develop more rational seismic design codes based upon a performance-based design concept, and to evaluate seismic performance of existing buildings. In my keynote lecture at the Korean Association for Computational Structural Engineering, the history of seismic design and use of structural analysis in Japan, the lessons for buildings from the Hyogoken-Nambu Earthquake, the

• Journal of Korean Society of Environmental Engineers
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• v.35 no.12
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• pp.937-942
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• 2013

Fluid generated within the sonic or ultrasonic waves are reflected by the wall, while the opposite direction forming a predetermined sound wave to the acoustic standing wave is referred to. In this study, the frequency of 1.0 MHz and 2.0 MHz acoustic standing wave generation module is installed in a continuous particle separation device, the laminar flow of influent, taking into account the hydraulic retention time (HRT) in accordance with changes in particle separation characteristics investigated. Operation of a standing wave in the particle separation device about $1.3{\sim}2.8^{\circ}C$ temperature is increased, but did not significantly affect the formation of standing waves. During operation, the HRT 1 hr frequency 1.0 MHz 2 hr, 4 hr longer as the particle separation efficiency (turbidity) were 64.1%, 70.0%, 74.3% and, 2.0 MHz has 58.0%, respectively, depending on HRT, 61.8%, 70.7% in the respectively. That is, the same frequency, the HRT treatment efficiency is 10% or more, depending on differences in generation and, 1.0 MHz frequency, 2 hr, 2.0 MHz 4 hr at about 70% or more of the processing efficiency can be maintained. Frequency of 1.0 MHz and 2.0 MHz operation at the same time, as a result, HRT 1 hr, 2 hr, 4 hr particle separation efficiency of 63.8%, respectively, 70.6%, 77.6%, rather than the generation of standing waves appear continuous HRT is affecting a lot of particles to separate could know.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.8
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• pp.8-18
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• 2003

An experimental study is carried out to investigate the Reynolds number effects on the near-wake of an airfoil oscillating in pitch. An NACA 4412 airfoil is sinusoidally pitched about the quarter chord point between the angle of attack -6$^{\circ}$ and +6$^{\circ}$. A hot-wire anemometer is used to measure the turbulent intensity in the near-wake region of an NACA 4412 airfoil. The freestream velocities of present work are 3.4, 12.4, 26.2 m/s, and the corresponding Reynolds numbers are $5.3{\times}10^4,\;1.9{\times}10^5,\;4.1{\times}10^5$ and the reduced frequency is 0.1. Axial turbulent intensity profiles are presented to show the Reynolds number effects on the near-wake region behind an airfoil oscillating in pitch. All the cases in these measurements show that the turbulent intensities by the change of the Reynolds number are very large at the lowest Reynolds number $R_N=5.3{\times}10^4$; and are small at the other Reynolds number $(R_N=1.9{\times}10^5\;and\;4.1{\times}10^5)$ in the near-wake region. The significant difference of turbulent intensity between $R_N=5.3{\times}10^4,\;and\;1.9{\times}l0^5$ is observed. A critical value of the Reynolds number in the near-wake of an oscillating NACA 4412 airfoil which indicates laminar separation, no separation or turbulent separation exists in the range between $R_N=5.3{\times}10^4\;and\;1.9{\times}10^5$.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.18 no.1
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• pp.33-38
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• 2010

Developments of numerical methods are very important to design and analysis for a high subsonic turbine blade. In general, Analysis by experimental investigation has needed a lot of human resources and required time, indispensably, and equipments still have a limit to measure in conditions of high temperature. Rapid technological developments of CPU and integration level of memory make it possible to advance computation with almost exactly simulation so, recent developments of numerical methods are in spotlight. In the present study, the panel method, which is well-known as relatively simplified numerical method, and 2-dimensional ordinary differential Falkner-Skan equation were computed in order to analyze the outer flow, and FVM-based solid heat transfer equation, was also computed to forecast the temperature distribution of the airfoil and the turbine blade. Unstructured grid was constructed in the turbine blade, which has double cooling holes, in order to analyze the internal heat transfer. Cooling fluid was assumed as fully-developed turbulent flow and that circulated in cooling holes.

• Korean Journal of Air-Conditioning and Refrigeration Engineering
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• v.9 no.3
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• pp.312-322
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• 1997

The natural convective flow in a two-dimensional square enclosure with horizontal partitions is investigated numerically. The enclosure was composed of the lower hot and the upper cold horizontal walls and the adiabatic vertical walls, and two identical partitions were positioned perpendicularly at the mid-height of the right and left walls, respectively. The governing equations are solved by using the finite element method with Galerkin method. Calculations are made for different partition lengths, partition conductivites, and Rayleigh numbers based on the temperature difference between two horizontal walls and the enclosure height with water(Pr=4.95). An oscillatory motion of the natural convective flow is affected significantly by the variation of the gap width and Rayleigh number. When the gap width is comparatively short, the heat transfer rate is raised with the increase of the thermal conductivity of partitions. However, for sufficiently large gap widths at higher Rayleigh numbers, the average Nusselt numbers of the conductive partitions are smaller than those of the adiabatic partitions.

• Journal of the Korean Society of Visualization
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• v.4 no.2
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• pp.44-50
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• 2006

A visualization study on the boundary layer and near-wake of an NACA 0012 airfoil was con-ducted in order to investigate the influence of boundary layer behavior on the near-wake at low Reynolds numbers. The present study is investigated at static angles of attack ${\alpha}=0^{\circ},\;3^{\circ},\;6^{\circ}$ and $Re=2.3{\times}10^4,\;3.3{\times}10^4,\;4.8{\times}10^4$ by using a smoke-wire technique. 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 that laminar separation of boundary layer on the airfoil surface occurs at ${\alpha}=3^{\circ}$. Furthermore, reattachment of the boundary layer occurs in the case of ${\alpha}=6^{\circ}$. In the current study, the location of the laminar separation point moves upstream as the Reynolds number and the angle of attack increase.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.14 no.4
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• pp.24-30
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• 2006

An experimental study was carried out in order to investigate the influence of boundary layer behavior on the near-wake at low Reynolds numbers. An X-type hot-film probe(55R51) was used to measure the near-wake of an NACA 0012 airfoil at static angles of attack ${\alpha}=0^{\circ}$, $3^{\circ}$, and $6^{\circ}$, and the Reynolds numbers Re=2.3${\times}10^4$, 3.3${\times}10^4$, and 4.8${\times}10^4$. The results of the study show that the characteristics of the boundary layer on the airfoil surface have a close relationship with the mean velocity and turbulence intensity profiles of a near-wake. Therefore, the development of the boundary layer, the position of the separation point, and the existence and non-existence of reattachment on the airfoil surface were represented by the differences in mean velocity and turbulence intensity profiles of the near-wake.