• Transactions of the Korean Society of Mechanical Engineers B
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• v.27 no.1
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• pp.105-116
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• 2003

The flow structure around the free end of a finite circular cylinder (FC) embedded in an atmospheric boundary layer (ABL) over open terrain was investigated experimentally with varying the free end shape. The experiments were carried out in a closed-return type subsonic wind tunnel. A finite cylinder with an aspect ratio (L/D) of 6 was mounted vertically on a long flat plate. The Reynolds number based on the cylinder diameter is about Re=7,500. The velocity fields near the FC free end were measured using the single-frame double-exposure PIV method. As a result, for the FC with a right-angled free end, there is a peculiar vortical structure, showing counter-rotating twin vortices near the FC free end. It is caused by the interaction between the entrained irrotational fluids from both sides of FC and the downwash flow from the FC free-end.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.19 no.4
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• pp.954-964
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• 2015

In this research, an overlapped illumination model was newly proposed for designing a freeform LED lens with a uniform illuminance distribution on its illuminating plane. Based on the proposed model and conventional illumination models, freeform lenses were designed and their performances and tolerances were compared. As a result of the tolerance analysis about thickness change in lens, position, size change, central direction change of light emission and characteristic change in LED source. This proposed model and divergent illumination model are similar to the performance about central direction change of light emission in LED source. but the uniformity illumination value in this proposed model is more remarkably value than it in divergent illumination model about characteristic change in LED source.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.12
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• pp.1097-1106
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• 2011

Unsteady numerical analysis was performed to simulate air-launched missiles from a complete helicopter in hover by using an unstructured overset mesh flow solver coupled with a module of six degree-of-freedom motion of equations. The unsteady computations have been performed to obtain flow fields around the complete helicopter including main rotor, tail rotor, and fuselage equipped with multiple missiles, and six-DOF simulation has been performed to predict the behavior of the air-launched missile. The effects of the launching position and the missile thrust on the trajectory of the missile were investigated as well as the aerodynamic interference of the air-launched missile under the unsteady downwash produced by main rotor.

• Journal of the Korean Society of Propulsion Engineers
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• v.5 no.4
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• pp.94-101
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• 2001

The shock structure of dual coaxial jet is experimentally investigated. Eight different kinds of coaxial, dual nozzles are employed to observe the major features of the near field shock structure on the supersonic, coaxial, dual jets. Four convergent-divergent supersonic nozzles having the Mach number 2.0 and 3.0 are used to compare the coaxial jet flows discharging from two sonic nozzles. The primary pressure ratio is changed in the range between 1.0 and 10.0, and the assistant jet ratio from 1.0 to 4.0. The results show that the impinging angle, nozzle geometry and pressure ratio significantly affect the near field shock structure, Mach disk location and Mach disk diameter.

• Transactions of the Korean Society of Mechanical Engineers
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• v.18 no.5
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• pp.1182-1191
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• 1994

This paper presents an enhanced method of slit beam projection intended for the rapid measurement of 3-dimensional surface profiles of dies and molds. Special emphasis is given to optimizing the design of optical system so that the measuring accuracy can be maximized by adopting two-plane camera calibration together with sub-pixel image processing techniques. Finally, several measurement examples are discussed to demonstrate that an actual measuring accuracy of $\pm$ 0.2 mm can be achieved over the measuring range of 500 mm{\times}300mm{\times}200mm$.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2001.04a
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• pp.328-331
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• 2001

Shape changes of a workpiece in an Eulerian Finite Element analysis for the steady state. three-roll-stand shape rolling are modelled. Although an Eulerian analysis has many advantages for the steady state rolling problems, it necessitates an assumption about the unknown shape of the control volume. In almost all cases. the assumed control volume does not match the final shape and the control volume should be updated. This update can be accomplished by performing a free surface correction. The final shape of a material point, which has a spherical shape at the inlet, can be also predicted by integrating a deformation gradient along a stream line. Analyses of three-roll-stand shape rolling is in detail examined.

• Proceeding of EDISON Challenge
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• 2012.04a
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• pp.33-36
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• 2012

풍력발전기 성능은 유동의 안정성과 풍속에 의해 결정되는데, 이때 유동 불안정성은 풍력발전기의 성능뿐만 아니라 구조적 문제를 함께 유발시킨다. 본 연구에서는 풍력발전기 타워 후류에서의 불안정성을 최소화시키기 위하여 타워 단면의 기초 형상설계 연구를 수행하였다. 기존의 풍력발전기 타워 형상에 부가 구조물을 설치함으로써 Karman vortex의 생성을 지연시키고 와류 간섭현상을 줄여 풍력발전기의 안정성을 증대시키고자 하였다. 이를 위해 다양한 타워 단면 형상에 대하여 양력계수 및 항력계수를 비교 분석하였다. 그 결과 반지름의 1/2 길이의 자유류 방향 tip과 splitter plate를 후방에 설치하는 것이 후류 불안정성을 억제하는데 가장 효율적인 것으로 나타났다.

• Journal of the Earthquake Engineering Society of Korea
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• v.5 no.1
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• pp.7-12
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• 2001

본 노문은 임의형상의 퇴적층을 갖는 반부한 영역내에서 SH하가 경사지게 입사할 때의 지진응답을 연구하였다. 그리고 비균질 퇴적층인 반무한 영역에서 파의 증폭을 다루었다. 사용한 수치해석 방법으로는 유한요소법과 경계요소법을 결합하여 수치해석하였다. 반무한 영역에서 자유장 응답과 정해를 비교 분석한 결과 잘 일치하여 검증되었다. 불규칙한 형상의 비균질 퇴적층을 갖는 부지에서의 지진응답 해석은 본 연구에서 개발한 수치해석 방법으로 가능하다. 따라서 임의 층상구조를 갖는 연약층에서의 SH파 증폭과 임의 각도와 입사하는 SH파에 대한 지진응답을 해석하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.275-278
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• 2010

By changing the nozzle throat area during the operation, thrust of a pintle thruster can be adjusted easily such as a liquid propulsion. In this paper, numerical analysis was carried out for SNECMA's pintle thruster with different pintle shapes. Flow field and aerodynamic load changed drastically with pintle shapes. Bore in the pintle decreased aerodynamic load significantly.

• Transactions of the Korean Society of Mechanical Engineers
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• v.17 no.5
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• pp.1202-1207
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• 1993

An optical method of slit beam scanning topography is presented for the 3-dimensional profile measurement of free-formed surfaces. A slit beam of laser is projected in a scanning mode and its illuminated trajectory on the object is captured by using a CCD camera. The 3-dimensional coordinates of the trajectory is then computed by using the given geometry between the slit beam and the camera, so that the whole surface profile of the object can be obtained in a successive manner. Detailed optical principles are described with special emphasis to lateral are discussed to demonstrate the measuring performances of the slit beam scanning topography proposed in this study.