• 한국항해항만학회지
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• 제34권6호
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• pp.429-434
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• 2010

해양의 다양한 환경에 노출된 선체 표면의 거칠기를 일반화 하여 모델 실험을 PIV기법을 적용하여 회류수조에서 수행하였다. 모델의 유동방향 표면 거칠기의 폭에 기초하여 본 연구에 적용된 레이놀즈수 Re=1.0$\times$103에서 유동가시화, 시간평균 속도장 및 와도장을 상호 평가를 통하여 유동특성을 조사하였다. 와의 생성과 소멸 메커니즘을 통해 와류의 중심은 표면 거칠기 높이의 0.5H로 나타났다. 또한 거칠기 계수가 증가함에 따라 와의 크기와 비례하고, 와의 생성위치도 상부와 전방으로 이동하였다.

• 한국자동차공학회논문집
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• 제12권6호
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• pp.38-45
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• 2004

This paper studies the effects of intake port configuration on the swirl that is key parameter in the flow field of direct injection diesel engines. In-cylinder flow characteristics is known to have significant effects on fuel air mixing, combustion and emissions. To investigate the swirl flow generated by various intake ports, steady state flow tests were conducted to evaluate the swirl. Helical port geometry, SCV shape and bypass were selected as the design parameters to increase the swirl flow and parametric study was performed to choose the optimal port shape that would generate a high swirl ratio efficiently. The results revealed that a key factor in generating a high swirl ratio was to suitably control the direction of the intake air flow passing through the valve seat. For these purposes, we changed the distance of helical and tangential port as well as installed bypass near the valve seat and the effects of intake port geometry on in-cylinder flow field were visualized by a laser sheet visualization method. From the experimental results, we found that the swirl ratio and mass flow rate had a trade off relation. In addition, the result indicates that the bypass is a effective method to increase the swirl ratio without sacrificing mass flow rate.

• 한국환경과학회지
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• 제28권11호
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• pp.1047-1059
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• 2019

To address the increase of weather hazards and the emergence of new types of such hazards, an optimization technique for three-dimensional (3D) representation of meteorological facts and atmospheric information was examined in this study as a novel method for weather analysis. The proposed system is termed as "meteorological and air quality information visualization engine" (MAIVE), and it can support several file formats and can implement high-resolution 3D terrain by employing a 30 m resolution digital elevation model. In this study, latest 3D representation techniques such as wind vector fields, contour maps, stream vector, stream line flow along the wind field and 3D volume rendering were applied. Implementation of the examples demonstrates that the results of numerical modeling are well reflected, and new representation techniques can facilitate the observation of meteorological factors and atmospheric information from different perspectives.

• 대한의용생체공학회:의공학회지
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• 제22권6호
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• pp.535-542
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• 2001

스텐트를 이용한 동맥류 색전술은 방추형 동맥류 등 목이 넓은 광경동맥류의 치료에 최근 사용되고 있다. 동맥류 내부의 혈류유동은 혈전의 형성 및 동맥류 폐색에 중요한 역할을 하므로 스텐트의 삽입으로 인한 동맥류 내부 혈류 유동의 변화를 고찰하기 위하여 광색성 염료를 이용한 유동가시화 방법을 사용하였다. 제작된 방추형 동맥류 모델에 대해 맥동 유동시 동맥류 벽 다섯 위치에서 유동장의 정성적 관탈 및 벽 전단변형률의 측정이 수행되었다. 스텐트의 삽입은 동맥류 내부의 유동을 감소시켰으며 동맥류 내부의 느린 와류유동이 감속후기가지 지속되었다. 또한 스텐트가 삽입된 모델은 스텐트가 없는 모델에 비하여 벽 전단변형률이 감소하였으며. OSI는 증가하였다 이러한 혈류유동의 변화는 혈전의 형성 및 내막거식증대가 일어나기 쉬운 혈류역학적 환경을 제공한다. 따라서 스텐트의 삽입으로 인한 동맥류 내부의 혈류 유동은 혈전의 형성 및 동맥류 폐색을 촉진하도록 변화함을 알 수 있었다..

• 대한기계학회논문집
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• 제18권3호
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• pp.690-700
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• 1994

The effects of thermal stratification on the flow of a stratified fluid past a circular cylinder were examined in a wind tunnel. In order to produce strong thermal stratifications, a compact heat exchanger type variable electric heater is employed. Linear temperature gradient of up to $250^{\circ}C/m$ can be well sustained. The velocity and temperature profiles in the cylinder wake with a strong thermal gradient of $200^{\circ}C/m$ were measured and the smoke wire flow visualization method was used to investigate the wake characteristics. It is found that the temperature field effects as an active contaminant, so that the mean velocity and temperature profiles can not sustain their symmetricity about the wake centerline when such a strong thermal gradient is superimposed. It is evident that the turbulent mixing in the upper half section is stronger than that of the lower half of the wake in a stably stratified flow.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2002년도 유체기계 연구개발 발표회 논문집
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• pp.433-438
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• 2002

The flow field around a symmetrical airfoil in a uniform flow under the generation of noise was numerically studied and compared with experimental datum. The numerical simulation was carried out by LES which employs a deductive dynamic model as subgrid-scale model. The result of an attack angle of $6^{\circ}$ indicate that the discrete frequency noise is generated when the separated laminar flow reattaches near the trailing edge of the pressure side and the turbulent boundary layer is formed over the suction side of the airfoil near the trailing edge. The periodic behavior of vortex formation was observed around the trailing edge and it persists further downstream in the wake. The frequency of the vortex formation in the wake was consistent with that of the discrete frequency noise.

• 한국항공운항학회지
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• 제18권4호
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• pp.86-91
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• 2010

New Design configurations of the fighter aircraft igloo diffuser were studied based on the closed ventilation type in contrast to the conventional open distribution type. To validate the enhanced and safe performance, the exhaust flow patterns of the two igloo diffuser types were simulated by both experimental and computational approaches as design tools. Flow visualizations were conducted to investigate the exhaust flow patterns in experimental approach. In addition, the commercial code called Fluent was used to calculate flow field properties. Computational simulations provided detailed parametric studies that significantly reduced the amount of experimentation necessary to alter the design parameters of the existing fighter igloo diffuser. The closed ventilation type of the igloo diffuser was shown the better results.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2002년도 학술대회지
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• pp.743-746
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• 2002

Experimental investigation of the flow field of supersonic cavity is described. In this research, supersonic cavity is used in chemical laser system. For efficient laser, downstream flow after cavity need to be uniform and clear for pressure recovery system. In previous research, it's known that there's oscillation In cavity and is due to Mach number and L/D ratio. A strong recompression occurs at the after wall and the flow is visibly unsteady. Cavity flow in this research is of the open type, that is, length-to-depth ratio $L/D<10\;at\;M\;=\;3$. Experiment is done with pressure measurement by piezo-type sensor and visualization by Schlirern method. The time-dependent experimental result is compared with computation.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2006년도 춘계학술대회논문집
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• pp.392-395
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• 2006

The configuration of coaxial co-rotating contained in shroud provides a useful model for investigating the characteristics of flow in the HDD. Reynolds number is defined as $Re_R={\Omega}{R_o}^2/{\upsilon},\;Re_H={\Omega}R_oH/{\upsilon}$ in present study. An experimental investigation was performed for turbulence profiles and PSD distribution and vortices frequency behavior for various range of $Re_R=2.43{\times}10^4{\sim}3.61{\times}10^5$. A laser Doppler anemometry (LDA) is used to obtain the velocity field of unobstructed co-rotating disks flow. Airflow pattern visualization between inner and outer region was compared with turbulence profiles measured from LDA. Outer detached shear layer and dead-zone without oscillating velocity fluctuation to circumferential mean were quantitively traced.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2002년도 추계 학술대회논문집
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• pp.28-34
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• 2002

A computational study of supersonic flow around lateral jet controlled missile has been performed. For this study, three dimensional Navier-Stokes code(AADL3D) has been developed. Spalart-Allmaras one equation turbulence model has been implemented on the AADL3D code for relatively rapid computational time. For the validation of developed code, AADL3D, pressure distributions on an ogive-cylinder body has been compared with experimental data. Also, the shock structure of sonic jet on the flat plate in the supersonic flow field has been compared with experimental flow visualization result to see the analysis capability of freestream-jet interaction case. A case study has been performed through comparing the normal force coefficient and the moment coefficient of missile body for several jet flow conditions. Current results will be used to the optimum design of a lateral jet controlled missile.