• International Journal of Naval Architecture and Ocean Engineering
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• 제3권4호
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• pp.242-253
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• 2011

Skin frictional drag reduction efficiency of "stiff" compliant coating was investigated in a wind tunnel experiment. Flat plate compliant coating inserts were installed in a wind tunnel and the measurements of skin frictional drag and velocity field were carried out. The compliant coatings with varying viscoelastic properties had been prepared using different composition. In order to optimize the coating thickness, the most important design parameter, the dynamic viscoelastic properties had been determined experimentally. The aging of the materials (variation of their properties) during half a year was documented as well. A design procedure proposed by Kulik et al. (2008) was applied to get an optimal value for the coating thickness. Along with the drag measurement using the strain balance, velocity and pressure were measured for different coatings. The compliant coatings with the thickness h = 7mm achieved 4~5% drag reduction within a velocity range 30~40 m/s. The drag reduction mechanism of the attenuation of turbulence velocity fluctuations due to the compliant coating was demonstrated. It is envisioned that larger drag reduction effect is obtainable at higher flow velocities for high speed trains and subsonic aircrafts.

• 한국철도학회:학술대회논문집
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• 한국철도학회 2011년도 춘계학술대회 논문집
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• pp.14-19
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• 2011

Wind tunnel tests are performed so as to investigate the aerodynamic drag characteristics of HEMU-400x, next generation Korean high speed train. The experiments of 1/20 scaled 5-car train model are done at 30, 40, 50, 60m/s with a normal bogie, a bogie cover, and a streamlined shape. The flat plate with knife edge are installed to minimize the effect of boundary layer of wind tunnel for the train model. The aerodynamic drag reduction was more by a streamlined shape than by a bogie cover from a normal bogie. Based on the experimental results, the aerodynamic drag of HEMU-400x test train(6-car) was predicted. It is prediceted that More bogie cover could reduce more aerodynamic drag of the test train in replacement of normal bogies.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2004년도 춘계학술대회
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• pp.1358-1363
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• 2004

The objective of this work is to propose calibration facility in which a thin film type heat flux sensor can be calibrated under convective flow condition by using a small wind tunnel with the constant temperature plate condition. A small wind tunnel has been built to produce a boundary layer shear flow above a constant temperature copper plate. 12-independent copper blocks, thin film heaters, insulators and temperature controllers were used to keep the temperature of flat plate constant at a specified temperature. Three commercial thin film-type heat flux sensors were tested. Convective calibrations of these gages were performed over the available heat flux range of $1.4{\sim}2.5kW/m^2$. The uncertainty in the heat flux measurements in the convective-type heat flux calibration facility was ${\pm}2.07%$. Non-dimensional sensitivity is proposed to compare the sensitivity calibrated by manufacturer and that of experiment conducted in this study.

• Wind and Structures
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• 제20권1호
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• pp.37-58
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• 2015

As wind flows around a sharp-edged body, the resulting separated flow becomes complicated, with multiple separations and reattachments as well as vortex recirculation. This widespread and unpredictable phenomenon has long been studied academically as well as in engineering applications. In this study, the flow characteristics around rectangular prisms with five different aspect ratios were determined through wind tunnel experiments and a detached eddy simulation, that placed the objects in a simulated deep turbulent boundary layer at $Re=4.6{\times}10^4$. A series of rectangular prisms with the same height (h = 80 mm), different longitudinal lengths (l = 0.5h, h, and 2h), or different transverse widths (w = 0.5h, h, and 2h) were employed to observe the effects of the aspect ratio. Furthermore, five wind directions ($0^{\circ}$, $10^{\circ}$, $20^{\circ}$, $30^{\circ}$, and $45^{\circ}$) were selected to observe the effects of the wind direction. The simulated results of the surface pressure were compared to the wind tunnel experiment results and the existing results of previous papers. The vortex and spectrum were also analyzed to determine the detailed flow structure around the body. The paper also highlights the pressure distribution around the rectangular prisms with respect to the different aspect ratios. With an increasing transverse width, the surface suction pressure on the top and side surfaces becomes stronger. In addition, depending on the wind direction, the pressure coefficient experiences a large variation and can even change from a negative to a positive value on the side surface of the cube model.

• Wind and Structures
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• 제7권1호
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• pp.1-12
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• 2004

Numerical simulation of flow past two-dimensional hill and valley is presented. Application of three turbulence models - the standard and modified (Kato-Launder) $k-{\varepsilon}$ models and standard $k-{\omega}$ model - is discussed. The computational methodology is briefly described. The mean velocity and turbulence intensity profiles, obtained from numerical simulations of flow past the hill, are compared with the experimental data acquired in a boundary-layer wind tunnel at Colorado State University. The mean velocity, turbulence kinetic energy and Reynolds shear stress profiles from numerical simulations of flow past the valley are compared with published experimental data. Overall, the results of simulations employing the standard $k-{\varepsilon}$ model were found to be in a better agreement with the experimental data than those obtained using the modified $k-{\varepsilon}$ model and the $k-{\omega}$ model.

• 한국산학기술학회논문지
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• 제17권11호
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• pp.363-367
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• 2016

본 연구는 마하수 2.5의 초음속 영역에서 마하수 1.0의 슬롯 분사가 있는 후향계단 형상에 대한 유동장 특성을 분석하기 위하여 초음속풍동 시험부를 설계, 제작하였다. 비행체가 고속으로 움직일 때 공동 주위의 유동은 매우 복잡하여 수치해석 결과를 검증할 초음속풍동 시험 자료가 필요하기 때문에 기존의 2차원 대칭형 노즐을 아랫면이 평판인 비대칭형 노즐로 수정하였다. 특성곡선해법을 이용한 비점성 노즐을 설계하고, 시험을 통해 얻은 경계층 두께를 노즐에 반영하여 보정한 기법을 C 언어로 프로그래밍하여 얻은 결과를 수치해석 결과와 비교하여 검증하였다. 슬롯 분사 시 지속적인 유동장 변화 분석을 위한 초음속 유지시간 확보를 위해 저장탱크의 압력 변화에 따른 PID 제어프로그램 수정으로 초음속 유동 유지시간을 약 5초에서 약 6초로 1초 정도 연장하여 제어 효율을 향상하였고, 슬롯 분사가 있는 후향계단에서의 유동장 변화를 슐리렌장치로 가시화하여 복잡한 유동장 특성을 확인하였다. 향후 슬롯 분사의 속도와 유량, 유동장의 온도를 변화하여 공동에서의 막냉각 효과 분석을 위한 장비로 사용할 계획이다.

• Wind and Structures
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• 제21권5호
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• pp.537-564
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• 2015

Excessive motions in buildings cause occupants to become uncomfortable and nervous. This is particularly detrimental to the tenants and ultimately the owner of the building, with respect to financial considerations. Serviceability issues, such as excessive accelerations and inter-story drifts, are more prevalent today due to advancements in the structural systems, strength of materials, and design practices. These factors allow buildings to be taller, lighter, and more flexible, thereby exacerbating the impact of dynamic responses. There is a growing need for innovative and effective techniques to reduce the serviceability responses of these tall buildings. The current study considers a case study of a real building to show the effectiveness and robustness of the TLD in reducing the coupled lateral-torsional motion of this high-rise building under wind loading. Three unique multi-modal TLD systems are designed specifically to mitigate the torsional response of the building. A procedure is developed to analyze a structure-TLD system using High Frequency Force Balance (HFFB) test data from the Boundary Layer Wind Tunnel Laboratory (BLWTL) at the University of Western Ontario. The effectiveness of the unique TLD systems is investigated. In addition, a parametric study is conducted to determine the robustness of the systems in reducing the serviceability responses. Three practical parameters are varied to investigate the robustness of the TLD system: the height of water inside the tanks, the amplitude modification factor, and the structural modal frequencies.

• 한국항공우주학회지
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• 제36권5호
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• pp.407-419
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• 2008

본 연구에서는 축 대칭 원뿔 형상 위의 압축성 경계층의 천이 지점을 선형 안정성 이론과 -method를 이용하여 예측하였다. 축 대칭 좌표계에서의 압축성 유동 지배 방정식으로부터 압축성 원뿔 경계층의 선형 안정성 방정식을 얻었으며 안정성 방정식을 2차 정확도의 유한 차분법을 이용하여 계산하는 수치 프로그램을 개발하였다. 개발 된 코드로 원뿔 경계층의 안정성 특성 및 2차원 교란의 증폭률을 계산하고 실험결과와의 비교를 통해 검증을 수행하였다. 얻어진 교란의 증폭률을 활용하여 -method를 통해 천이지점 예측을 수행하였다. 풍동 시험 및 비행 시험 결과와의 비교를 통해 비행 조건에 있는 마하수 4와 8사이의 원뿔 경계층에 대한 본 연구의 천이지점의 예측 능력을 확인하였다. 또한 벽면 냉각이 경계층 내부 교란의 안정성 및 천이 지점에 미치는 영향을 분석하였다.

• Wind and Structures
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• 제24권6호
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• pp.657-677
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• 2017

This paper discusses some features and conditions that characterize the Zonda wind, focusing particularly on the implications for wind engineering applications. This kind of wind, typical of mountainous regions, is far from being adequately characterized for computational simulations and proper modeling in experimental facilities such as boundary layer wind tunnels. The objective of this article is to report the research works that are being developed on this kind of wind, describing the main obtained results, and also to establish some general guidelines for the proper analysis of the Zonda in the wind engineering context. A classification for the Zonda wind is indicated and different cases of structural and environmental effects are described. Available meteorological data is analyzed from the wind engineering point of view to obtain the Zonda wind gust factors, as well as basic wind speeds relevant for structural design. Some considerations and possible directions for the Zonda wind-tunnel and computational modeling are provided. Gust factor values larger than those used for open terrain were obtained, nevertheless, the basic wind speed values obtained are similar to values presented by the Argentinian Wind Code for three-second gust, principally at Mendoza airport.

• 에너지공학
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• 제12권2호
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• pp.131-138
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• 2003

본 연구에서는 평판 경계층의 천이 영역에서 평균속도, 표면마찰계수, 간헐도 분포, 에너지 스펙트럼 등의 신뢰성 있는 실험 자료를 획득하였다. 실험 결과 천이가 진행됨에 따라 난류반점이 지배하는 영역이 벽면 근처에서 전 경계층으로 확산되었으며 이러한 현상의 결과로 속도 섭동량에서 비등방성이 크게 나타난다. 천이 이전영역에서는 에너지가 주로 저주파에 집중되어 있다가 천이를 거치면서 에너지가 고주파 성분으로 이동하였다 이는 두 가지 이상의 에너지 발생과 소멸 메커니즘이 천이영역에서 공존하고 있음을 의미한다. 따라서 천이영역에서의 유동장을 예측하기 위한 난류 계산 모형에서 비등방성과 서로 다른 메커니즘을 표현할 수 있기 위해서는 반드시 두 가지 이상의 척도를 표현할 수 있어야 한다.