• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2010년도 제35회 추계학술대회논문집
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• pp.451-458
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• 2010

한국항공우주연구원의 스크램제트 엔진 시험설비(이하 SETF)는 극초음속 추진기관 성능시험 설비로 일반 공력 풍동과 달리 엔진이 구동하는 비행 고도, 마하수에서의 엔탈피를 모사해야 한다. SETF는 불어내기 식으로 고압공기 공급원으로부터 공급된 고압 공기를 축열식 가열시스템으로 가열시킨 후 시험부에 장착된 노즐을 통과. 팽창하여 엔진 시험 조건을 모사하며, 공기 이젝터를 구동하여 고고도 조건과 설비 시동 조건을 구현한다. SETF의 시험부는 자유제트 형식으로 시험엔진 시작점을 노즐 출구면에 일치시킬 경우 비행체에서 발생되는 경계층과 엔진의 상호 작용을 파악할 수 있는 반면, 설비 시동 특성을 예측하기 힘들어 시험을 통한 설비 특성 파악이 필수적이다. 본 논문에는 SETF의 마하수 및 시험 모델 변화에 따른 시동 성능 그리고 시동 성능 개선을 위하여 수행된 이젝터 설계 변경 과정을 정리하였다.

• 한국항공우주학회지
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• 제41권9호
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• pp.700-707
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• 2013

0.4 MW 급 분절형 아크 히터를 장착한 전북대학교 플라즈마 풍동의 초음속 유동 특성 실험을 수행하고 그 결과를 분석하였다. 실험에 사용된 분절형 아크 히터와 초음속 노즐은 16.3 g/s 의 질량유량에 대해 전극 당 150 A, 전체 300 A의 입력전류 조건으로 운전되었으며, 운전 결과 350 kW의 입력전력과 약 51.4 %의 열효율이 계측되었다. 이 때, 아크 히터 내 고엔탈피 플라즈마의 내부압력은 약 4 bar 로 측정되었으며, 이를 초음속 노즐을 통해 압력 45 mbar로 유지되는 진공쳄버 내로 팽창시킴으로써, 전체 엔탈피 11 MJ/kg을 가진 초음속 플라즈마 유동을 얻을 수 있었다. 전체 엔탈피 측정과 함께, 생성된 초음속 플라즈마 유동에 대해 원뿔각 $30^{\circ}$를 가진 원뿔 탐침을 삽입하여 경사 충격파와 이루는 각을 측정하였으며, 이 측정값들로부터, 발생된 초음속 플라즈마의 온도와 마하 수는 각각 약 2,950 K 및 약 3.7에 이를 것으로 예상되었다.

• Wind and Structures
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• 제32권4호
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• pp.371-391
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• 2021

Tornadoes are the most devastating meteorological natural hazards. Many empirical and theoretical numerical models of tornado vortex have been proposed, because it is difficult to carry out direct measurements of tornado velocity components. However, most of existing numerical models fail to explain the physical structure of tornado vortices. The present paper proposes a new empirical numerical model for a tornado vortex, and its load effects on a low-rise and a tall building are calculated and compared with those for existing numerical models. The velocity components of the proposed model show clear variations with radius and height, showing good agreement with the results of field measurements, wind tunnel experiments and computational fluid dynamics. Normal stresses in the columns of a low-rise building obtained from the proposed model show intermediate values when compared with those obtained from existing numerical models. Local forces on a tall building show clear variation with height and the largest local forces show similar values to most existing numerical models. Local forces increase with increasing turbulence intensity and are found to depend mainly on reference velocity Uref and moving velocity Umov. However, they collapse to one curve for the same normalized velocity Uref / Umov. The effects of reference radius and reference height are found to be small. Resultant fluctuating force of generalized forces obtained from the modified Rankine model is considered to be larger than those obtained from the proposed model. Fluctuating force increases as the integral length scale increases for the modified Rankine model, while they remain almost constant regardless of the integral length scale for the proposed model.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2009년 춘계학술대회논문집
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• pp.19-19
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• 2009

Dynamic Stall is a flow phenomenon which occurs on the retreating side of helicopter rotor blades during forward flight. It also occurs on blades of stall regulated wind turbines under yawing conditions as well as during gust loads. Time scales occurring during this process are comparable on both helicopter and wind turbine blades. Dynamic Stall limits the speed of the helicopter and its manoeuvrability and limits the amount of power production of wind turbines. Extensive numerical as well as experimental investigations have been carried out recently to get detailed insight into the very complex flow structures of the Dynamic Stall process. Numerical codes have to be based on the full equations, i.e. the Navier-Stokes equations to cover the scope of the problems involved: Time dependent flow, unsteady flow separation, vortex development and shedding, compressibility effects, turbulence, transition and 3D-effects, etc. have to be taken into account. In addition to the numerical treatment of the Dynamic Stall problem suitable wind tunnel experiments are inevitable. Comparisons of experimental data with calculated results show us the state of the art and validity of the CFD-codes and the necessity to further improve calculation procedures. In the present paper the phenomenon of Dynamic Stall will be discussed first. This discussion is followed by comparisons of some recently obtained experimental and numerical results for an oscillating helicopter airfoil under Dynamic Stall conditions. From the knowledge base of the Dynamic Stall Problems, the next step can be envisaged: to control Dynamic Stall. The present discussion will address two different Dynamic Stall control methodologies: the Nose-Droop concept and the application of Leading Edge Vortex Generators (LEVoG's) as examples of active and passive control devices. It will be shown that experimental results are available but CFD-data are only of limited comparison. A lot of future work has to be done in CFD-code development to fill this gap. Here mainly 3D-effects as well as improvements of both turbulence and transition modelling are of major concern.

• 한국수자원학회논문집
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• 제56권2호
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• pp.125-137
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• 2023

지속적으로 증가하는 플라스틱의 사용으로 인하여 현재 해안·해양 환경에서 플라스틱을 찾기란 어렵지 않은 일이 되었다. 하천을 통해 해양으로 유출된 플라스틱 폐기물은 해안 지역에서 장기간 머물며, 파랑, 바람, 유사, 인간 활동 등과 같은 다양한 요인들과 상호작용하며 물리적·화학적 변화를 겪게 된다. 이에, 실험적 연구를 통하여 해안 유사에서 수체로의 플라스틱 입자 방출 과정을 고찰하고자 하였다. 본 연구는 고 레이놀즈 수를 가지는 왕복 흐름과 유사 이동을 구현하기 위한 왕복흐름발생장치를 제작하여 진행되었고, 세 가지의 크기를 가지는 매끈한 구형의 플라스틱 입자를 사용하였다. 실험 결과, 유사 내 플라스틱 입자의 방출은 유사 이동에 가장 큰 영향을 받았으며, 이는 흐름의 세기에 비례한다. 더불어, 입자가 작을수록 더 많은 입자가 방출되었다. 결과를 종합하여 입자의 방출을 결정하는 무차원 매개변수들의 임계값을 제시하였다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2006년도 제27회 추계학술대회논문집
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• pp.387-392
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• 2006

본 연구에서는 초음속 충동형 터빈의 유동특성을 알아보기 위해 소형 초음속 풍동을 설계하였다. 실험은 익렬 위치에 따른 초음속 터빈의 유동 특성을 파악하고 확산 손실이 발생하는 특성을 알기 위해 익렬의 위치를 조절해가며 2차원 초음속 노즐과 익렬을 조합하여 실시하였다. Z-type 슐리렌(Schlieren) 시스템을 이용하여 유동을 가시화 하였다. 이러한 실험을 통해 충격파를 포함한 복잡한 유동 형태와 유동박리, 충격파-경계층 상호작용 등을 관찰할 수 있었다.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2008년도 춘계학술대회논문집
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• pp.637-640
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• 2008

Noise generated from maglev vehicles mainly consists of two components, one is due to mechanical noise and the other due to aerodynamic noise. The former is due to the vehicle-guideway interactions and the latter results from the unsteady air flow around the vehicle. Aerodynamic noise could become more predominant around 225 km/h for maglev vehicles. In this paper, the aerodynamic noise of maglev vehicles is investigated experimentally. The results of the wind tunnel experiments of maglev vehicle models are introduced and compared. The comparison shows that the position of the main noise is between the bottom of the vehicle model and the rail. It is also found that the emitted sound pressure level is related to the gap size between the vehicle bottom and the rail.

• 대한설비공학회:학술대회논문집
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• 대한설비공학회 2009년도 하계학술발표대회 논문집
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• pp.1153-1158
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• 2009

The performance of louver-finned flat-tube and fin & tube radiators for computer CPU liquid cooling were experimentally investigated. In this study, 7 samples of radiators with different shape and pass number (1, 2, 10) were tested in a wind tunnel. The experiments were conducted under the different air velocity range from 1 to 4 m/s. The water flow rate through a pass was 1.2 LPM. Inlet temperatures of air and water were $20^{\circ}C$ and $30^{\circ}C$ respectively. It was found that the best performance was observed in the louver-finned flat-tube sample considering pressure drop and heat transfer coefficient.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2003년도 추계학술대회
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• pp.408-413
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• 2003

Naphthalene sublimation technique is used to investigate the average and local heat transfer from the circular rod, and to determine the average and local heat transfer from the circular rod with and without square wing type mixing vane in axial flow. The experiments are performed for a circular rod and flat plate with and without mixing vane in wind tunnel. In comparison with flat plate and circular rod in axial flow, averaged Nusselts number is increased 2 times as the increase of Reynolds number with mixing vane. Longitudinal vortex induced by square wing type has the stronger vortex strength, so square wing type vortex generator shows an effect further in downstream.

• 한국CDE학회논문집
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• 제2권2호
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• pp.85-92
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• 1997

An axial flow fan design system has been made by integrating the self-developed programs and I-DEAS. By using the system, an axial flow fan was designed, manufactured and verified through the wind tunnel experiments in coorperation with a refrigerator appliance division. It has been shown that the optimal design without the ambiguity of the design parameters can be possible by the three-dimensional flow simulations using a self-developed CID code, FANS-3D. (Flow Analysis code using Navier Stokes aguations in Three-Dimensional curvilinear coordinates). By virtue of the fluency of the data flow, an optimally designed fan which satisfies design conditions can be selected in a short time and less cost. The manufacturing processes of a Mock-up and an injection molding die have been automated through the self-made interface programs which connnect from the start to the end. It has been shown that the newly developed fan by this system has a superior performance characteristics to an existing fan.