• 대한기계학회논문집
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• 제11권3호
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• pp.444-453
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• 1987

본 연구에서는 난류구조에 대한 유선곡률의 영향을 명확히 반영하는 적절한 곡률수정 2-방정식모델을 개발하고자 한다. 이 연구에서 제안된 모델의 타당성은 다 음의 2차원 재순환유동에 대한 실험결과와 계산결과의 비교를 통해서 입증될 것이다. (1) Moss와 Bake에 의하여 맥동열선 풍속계로 측정된 두꺼운 수직벽주위의 유동` (2) 레이저 도플러 속도계로 Fraser와 Siddig에 의해 측정된 얇은 수직벽유동` (3)맥동열 선 풍속계로 Eaton이 실험한 후면벽유동` (4)맥동열선 풍속계로 Moss와 Baker가 측정 한 전면벽유동. 새로운 곡률수정 2-방정식모델은 2장에서 설명되고 있으며, 3장에서 는 경계조건과 수치계산 과정이 간단이 기술되어 있다. 그 뒤에 4장에는 계산결과와 실험치에대한 비교검토가 설명되어 있고 마지막으로 5장에서는 본 연구에 대한 결론을 맺고 있다.

• 대한기계학회논문집
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• 제18권7호
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• pp.1851-1865
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• 1994

The objective of the present study is to predict the film cooling effectiveness by a row of holes at various injection ratios and injection angles. Numerical calculations have been performed to investigate the characteristics of flow and temperature distributions in a region near the down-stream of injection hole including the region of adverse pressure gradient. The elliptic turbulent 3-dimensional governing equations with variable thermal properties using the low-Reynolds number k-$\bar{varepsilon}$ model was solved by SIMPLE algorithm. The results showed that the presence of adverse pressure gradient and secondary vortex in the region near the downstream of injection hole induces large temperature gradent. The $45^{\circ}$ injection has higher averaged film cooling effectiveness than $60^{\circ}$ injection. But neverthless the $90^{\circ}$ injection has greater deviation from a flat plate than $45^{\circ}$ and $60^{\circ}$ injection, the $90^{\circ}$ injection has higher averaged film cooling effectiveness than $45^{\circ}$ and $60^{\circ}$ injection in the region near the downstream of injection hole.

• 대한기계학회논문집B
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• 제26권8호
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• pp.1153-1163
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• 2002

A transient analysis on temperatures of fuel and oil in hydraulic and lubrication systems in an aircraft was studied using the finite difference method. Numerical calculation was performed by an explicit method with modified Dufort-Frankel scheme. Among various missions, air superiority mission was considered as a mission model with 20% hot day ambient condition in subsonic region. The ambience of the aircraft was assumed as turbulent flow. Convective heat transfer coefficient were used in calculating heat transfer between the aircraft surface and the ambience. For an aircraft on the ground, an empirical equation represented as a function of free-stream air velocity was used. And the heat transfer coefficient for flat plate turbulent flow suggested by Eckert was employed for in-flight phases. The governing equations used in this analysis are the mass and energy conservation equations on fuel and oils. Here, analysis of fuel and oil temperature in the engine was not carried out. As a result of this analysis, the ground operation phase has shown the highest temperature and the largest rate of temperature increase among overall mission phases. Also, it is shown that fuel flow rate through fuel/oil heat exchanger plays an important role in temperature change of fuel and oil. This analysis could be an important part of studies to ensure thermal stability of the aircraft and can be applicable to thermal design of the aircraft fuel system.

• 대한기계학회논문집B
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• 제26권11호
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• pp.1613-1621
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• 2002

An electromagnetic flowmeter(EMF) essentially averages the velocity distribution over the pipe cross- sectional area, and the measured value is dependent on the velocity profiles. In this study, installation effects of 90$^{\circ}$long elbow(KS B 1522, ISO 3419) on the EMF characteristics was investigated. A commercial EMF was adopted and the distribution of magnetic field in the electrodes cross section was measured. In the experiment, the national flow standard system, of which measurement uncertainty was evaluated in accordance with ISO 17025 recommendation, was used fur characterization of EMF. The leading line has 150D long straight pipe to established a fully developed flow before entering into the elbow and the elbow was installed downstream of it. then the flowmeter was tested within 50 D from the elbow. The installation effects of the flowmeter were investigated by varying the mean velocity(Reynolds No.)in pipe section, the locations and the direction of electrodes plane.($\phi$) From the experimental results, we find the optimal conditions to get most accurate measurements. Generally, the deviations from the calibration value were less than 0.5 % in farther than 10D distance from the elbow and the direction of electrode plane. $\phi$ = 90$^{\circ}$yielded the smallest measurement deviation. These characteristics were shown consistently in turbulent region regardless of the mean Reynolds number.

• 대한토목학회논문집
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• 제14권6호
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• pp.1365-1373
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• 1994

난류전단 흐름에서의 기포 크기분포를 예측하기 위하여 개발된 Monte-Carlo 모의모형을 실험실 크기의 문제에 적용하였다. 각종 모형 매개변수 및 물리적 변수들에 대한 민감도 분석을 수행하였으며, 실험 관측치와의 비교를 통하여 모형의 실제 적용성에 관하여 조사하였다. 공기와 물의 유량비 또는 마찰계수가 증가함에 따라 기포의 크기가 커지는 것으로 나타났다. 평균유속이 증가함에 따라 가포의 크기는 작아지지만, 폭기구간내 기포의 총표면적은 거의 일정함을 보였다. 모형의 종방향 거리증분에 따른 기포 크기분포의 변화는 거의 없었으며, 횡방향 거리중분을 크게 할수록 기포가 크거나 작은 쪽으로 치우쳐 중간정도의 크기를 갖는 기포의 수가 감소하였다. 기포의 크기분포는 그 초기분포 및 공기의 주입위치에 크게 영향을 받는 것으로 나타났다. 기포의 충돌과 응집을 구분하기 위하여 충돌효율을 도입하였다.

• 한국음향학회지
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• 제23권5호
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• pp.340-352
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• 2004

28.5 ㎑의 초음파의 미세 수직진동에 의해서 유도된 음향유동 (acoustic streaming)을 레이저를 이용한 입자 영상. 유속계에 의하여 고정 유리 평판과 초음파 진동자의 사이에서의 공기 유동을 가시화 하였다. 음향유동에 의한 공기의 유동 속도의 증가를 측정하기 위해 고정 유리 평판과 초음파 진동자의 사이에서의 속도변화를 실시간으로 측정하였다. 진동자와 고정 평판의 사이의 gap에 따른 음향유동의 세기의 변화를 정량적인 공기의 유동 속도의 변화에 의해 관찰되었고 고정판과 초음파 진동자 사이의 gap에서 공진 상태를 야기시키는 공진 Gap (H=18, 24, 30, 36㎜)중에서 공진 Gap (H)이 18m일 때 최대의 음향속도가 존재함을 알 수 있었고 진동자 표면부근에서부터 고정평판사이까지의 국소 최대 난류강도의 축 방향 위치에 따른 변화는 gap의 크기에 따라 8%∼70% 이었다. 전단응력값은 반경방향 위치의 중심영역에서 최대전단응력을 가지며 와도 분포도 반경방향 위치에서 진동자 중심영역에 최대 및 최소와도 값을 가짐을 알 수 있었다.

• 대한공업교육학회지
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• 제34권1호
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• pp.238-251
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• 2009

배열센서에 영향을 주는 자체소음은 그 시스템이 설치된 곳에서 발생하는 소음과 해양으로부터 들어오는 주변소음을 포함한 소음으로 정의된다. 수중에서의 탐지를 위한 배열 구조는 표면을 따라 발생되는 유체 유기소음에 많은 영향을 받는다. 본 논문에서는 곡면배열 음향 센서를 설계하기 위하여 유동유기 소음의 영향으로 인한 주파수 밀도 함수의 적분식의 주요 구성요소인 전달함수(transfer function)를 저파수 영역에서 수치해석 하였다. 난류 경계층에서 발생하는 유입 소음은 수정된 Corcos 모델을 이용하였다. 저파수 영역에서의 전달함수의 특성은 고정판의 두께와 밀도가 작아질수록 함수의 적분값은 적어지므로 소음의 영향은 줄어드는 것으로 나타났다. 또한 Corcos 벽면 압력과 전달함수의 곱에 따른 특성과 주파수 밀도 함수의 곱의 변화를 보였다. 향후 이러한 연구는 무인 잠수정에 탑재할 수 있는 곡면배열 센서의 설계에 응용이 가능하리라 판단된다.

• Journal of Advanced Marine Engineering and Technology
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• 제28권3호
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• pp.500-508
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• 2004

The heat transfer coefficients during gas cooling process of carbon dioxide in a horizontal tube were investigated. The experiments are conducted without oil in the refrigerant loop. The main components of the refrigerant loop are a receiver, a variable-speed pump, a mass flow meter, a pre-heater, and a gas cooler(test section). The water loop consists of a variable-speed pump, an isothermal tank, and a flow meter. The gas cooler is a counterflow heat exchanger by cooled water flowing in the annulus. The $CO_2$ flows in the horizontal stainless steel tube. which is 9.53mm in O.D. and 7.75mm in I.D. The gas cooler is 6 [m] in length. which is divided into 12 subsections, respectively. The experimental conditions considered in the study are following range of variables : refrigerant temperature is between 20 and $100^{\circ}C$. mass fluxes ranged from 200 to 400kg/($m^2$.s), average pressure varied from 7.5 to 10.0MPa. The main results were summarized as follows : The friction factors of $CO_2$ in the gas cooler show a relatively good agreement with those predicted by Blasius' correlation. The local heat transfer coefficient in the gas cooler has compared with most of correlations, which are the famous ones for forced convection heat transfer of turbulent flow. The results show that the local heat transfer coefficient of gas cooler agrees well with the correlation by Bringer-Smith except that at the region near pseudo critical temperature. while that at the near pseudo critical temperature is higher than the correlation.

• Journal of Mechanical Science and Technology
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• 제17권6호
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• pp.925-934
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• 2003

An experimental study is performed to investigate the characteristics of near wake flow behind a circular cylinder with serrated fins using a constant temperature anemometer and flow visualization. Various vortex shedding modes are observed. Fin height and pitch are closely related to the vortex shedding frequency after a certain transient Reynolds number. The through velocity across the fins decreases with increasing fin height and decreasing fin pitch. Vortex shedding is affected strongly by the velocity distribution just on top of the finned tube. The weaker gradient of velocity distribution is shown as increasing the freestream velocity and the fin height, while decreasing the fin pitch. The weaker velocity gradient delays the entrainment flow and weakens its strength. As a result of this phenomenon, vortex shedding is decreased. The effective diameter is defined as a virtual circular cylinder diameter taking into account the volume of fins, while the hydraulic diameter is proposed to cover the effect of friction by the fin surfaces. The Strouhal number based upon the effective diameters seems to correlate well with that of a circular cylinder without fins. After a certain transient Reynolds number, the trend of the Strouhal number can be estimated by checking the ratio of effective diameter to inner diameter. The normalized velocity and turbulent intensity distributions with the hydraulic diameter exhibit the best correlation with the circular cylinder's data.

• 대한기계학회논문집B
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• 제22권6호
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• pp.757-770
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• 1998

A Navier-Stokes code with a low Reynolds number k-.epsilon. turbulence model was tested to investigate its predictability for the unsteady transitional boundary layer flow due to rotor-stator interaction. A preliminary calculation with three different numbers of time steps 300, 600, and 1000 for a rotor wake passing period was carried out to see the effects of time steps on the unsteady flow and pressure fields due to rotor-stator interaction. Numerical solutions showed that unsteady pressure was much more sensitive to the number of time steps and over 600 time steps should be used to get a numerical solution independent of the number of time steps for a rotor wake passing period. The original low Reynolds number k-.epsilon. turbulence model showed very poor prediction of the unsteady transitional boundary layer flow due to rotor-stator interaction. This was due to the excessive production of turbulent kinetic energy near the leading edge. A modification suggested by Launder was incorporated and the modified model captured well the wake induced transitional strip. Present solutions also showed improved prediction over previous Euler/boundary layer solution in terms of the onset of unsteady transition and its extent.