• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.7
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• pp.647-654
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• 2010

In this study, an efficient ornithopter aerodynamic model, which is applicable to ornithopter wing design considering fluid-structure interaction or ornithopter flight dynamics and control simulation, was proposed and experimentally validated through the wind tunnel experiments. Due to the ornithopter aerodynamics governed by unsteady low Reynolds number flow, an experimental device was specially designed and developed. A part of the experimental device, 2-axis loadcell, was situated in the non-inertial frame; the dynamic calibration method was established to compensate the inertial load for pure aerodynamic load measurements. The characteristics of proposed aerodynamic model were compared with the experimental data in terms of mean and root-mean-square values of lift and drag coefficients with respect to the flow speed, flapping frequency, and fixed angle of attack.

• Journal of Korean Society of Steel Construction
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• v.23 no.1
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• pp.73-81
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• 2011

The wind force coefficient of a transmission tower frame shows several characteristics when the section shape, solidity ratio, and wind direction angle are changed. In this study, the wind force characteristics of a transmission tower frame with a basic structure were evaluated using different solidity ratios and wind direction angles in a wind tunnel test. According to the solidity ratio, the size of the structure and the rectangular-frame model of the transmission tower were changed by adding a two-dimensional (2D) or three-dimensional (3D) structure. The transmission tower's rectangular frame was tested by changing the wind direction angle of the 2D-type structure from 0 to $90^{\circ}$ and by changing the wind direction angle of the 3D-type structure from 0 to $45^{\circ}$ Based on the results that were obtained, it can be concluded that the wind force coefficient of a transmission tower frame can be used as preliminary data in deciding the transmission tower's wind load.

• Journal of Korean Society of Steel Construction
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• v.21 no.3
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• pp.289-299
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• 2009

This study summarizes basic results on the characteristics of mean wind pressure distribution on rectangular low-rise buildings with various breadths and depths through simultaneous multi-point wind pressure test. 5 types of rectangular wind pressure test models with various breadths and depths have been made for this study. Wind pressure tests are conducted on the Boundary Layer Wind Tunnel at Kumoh National Institute of Technology. The characteristics of mean wind pressure distribution with respect to various breadths and depths of low-rise buildings are analyzed into windward face, leeward face and side faces of building. From the results, new wind pressure coefficients and simplified wind load estimating formula for the resonable design of the structural frames of low-rise building were proposed.

• Proceedings of the Korea Air Pollution Research Association Conference
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• 2000.04a
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• pp.58-59
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• 2000

오존은 공간적.시간적 변동이 매우 큰 대기오염물질로 서울시의 27개 대기오염 자동측정망에서 실시간으로 측정.감시되고 있으며, 오존의 농도가 높아지는 여름철에는 오존경보제를 실시하고 있다. 특히 오존의 농도는 일사, 풍향, 풍속 등의 기상인자, $NO_x$, VOCs 등 전구물질의 농도, 그리고 지형에 따라서 영향을 받는 것으로 알려져 있다. 따라서, 본 연구에서는 서울지역에 대한 기하학적 축소모형을 제작하여 풍동내에서 풍향.풍속을 측정하여 지형에 따른 바람의 특성을 파악하였다. (중략)

• The Journal of the Korea Contents Association
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• v.10 no.11
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• pp.446-451
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• 2010

To investigate the vortex induced vibrations the 2-d.o.f. spring mounted circular cylinder was tested in the wind tunnel. The circular cylinder was designed to have the translational and the rotational mode uncoupled to each other. During the wind tunnel tests the resonance behaviors of the translational and the rotational modes by the locking-on phenomena were observed. From the locking-on phenomena observed it is shown that the vortex shedding is correlated with the responses of the structures. And the forces generated by the vortex shedding are influenced by the amplitudes and the frequencies of the cylinders.

• 한국항공운항학회:학술대회논문집
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• 2015.11a
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• pp.35-38
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• 2015

본 연구에서는 스포츠급 경항공기 모형의 공력 특성을 공군사관학교 아음속 풍동에서 측정하였다. 풍동시험은 유속 40m/s에서 이전 모델과 최근 공력성능 향상을 위해 보완된 모델에 대해 비교 실험 수행하였으며, 정확한 데이터를 얻기 위하여 흐름각 효과, 벽면효과, 지지대 간섭효과를 보정하여 공력계수를 산출하였다. 실험 결과, 두 모델의 항력계수와 양력계수가 전체적으로 유사한 경향성을 보이나 고받음각에서의 양력특성의 차이가 발생하였다. 또한 실제 비행 시의 레이놀즈 수 유동을 모사하기 위하여 Trip strip의 영향에 대하여 실험하였다. 그 결과 Trip strip을 부착하였을 경우 항력계수가 증가하고 최소항력받음각이 낮아지는 결과를 획득하였다.

• Proceedings of the Computational Structural Engineering Institute Conference
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• 2011.04a
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• pp.332-335
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• 2011

바람에 의해 발생하는 장대교량의 진동현상은 버펫팅과 와류진동 그리고 플러터 등으로 구분할 수 있으며, 특히 설계풍속에 해당하는 강풍에 안전한 교량을 설계하는 것이 주된 관심사항이다. 이러한 장대교량의 공기역학적인 안정성 검토에 사용되는 플러터 계수를 풍동실험을 통하여 산정하였다. 본 논문에서는 일반적인 플레이트 거더교의 강풍에 대한 안정성을 검토하기 위하여 풍동실험을 수행하였으며, 자유진동 기법과 강제진동 기법을 사용하여 추출한 플러터 계수를 비교하였다. 자유진동 기법은 교량단면에 초기변위를 주어 상하 및 회전 진동을 하는 교량단면의 변위를 측정한 후 system identification 기법으로 플러터 계수를 구하게 된다. 그리고 강제진동 기법은 상하방향의 강제진동과 회전방향의 강제진동 실험을 독립적으로 수행하여 교량단면에 작용하는 풍하중과 단면의 진동을 분석함으로써 플러터 계수를 추정하게 된다. 그리고 플러터 계수의 비교를 통하여 강제진동 기법과 자유진동 기법의 장단점을 분석하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.7
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• pp.575-580
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• 2007

During the conceptual design phase of a canard type high maneuverable aircraft, the low speed small scale wind tunnel test was conducted to investigate the high angle-of-attack static stability of the aircraft. In this study, 1/50th scale generic canard-body-wing model was used for the small scale wind tunnel test. For the analysis of static stability including high angle-of-attack nonlinear characteristics, the vertical tail effects were studied due to canard deflections. In addition, the nose chine effects were studied at high angle-of-attack. Based on the results obtained from the experimental study, the configuration change effects for canard type aircraft on high angle-of-attack static stability have been able to analyze.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.5
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• pp.93-99
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• 2003

The determination of thrust is essential in design and evaluation of a hypersonic airbreathing propulsion device. Conventional methods to determine the thrust is using thrust stand or force measurement system. However, these conventional methos are not applicable to the case where thrusts stands are impractical, such as free jet testing of engines, and model combustor. For this reason, the thrust determination method from measured pitot pressure is considered and validated. Validation of thrust determination from pitot pressures can be achieved by comparing the actual thrust from thrust stand. For validation purpose, a small-scale supersonic wind tunnel is installed on the thrust stand. Thrusts are measured while pressures are measured simulaneously. Then, the thrust from pitot pressure measurements are compared with the measured thrust and theoretical thrusts.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.6
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• pp.463-467
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• 2016

In this paper, acceleration and pressure exerted on a human model were measured under a supersonic condition in a shock tunnel. In order to measure these in an interference-free environment, free-fall technique with an electromagnet and a three-dimensional iron-powdered human model was used. Free-fall experiment was conducted at Mach 4 and the force acting on the model was obtained by calculating the displacement from the flow visualization images.