• Transactions of the Korean Society of Mechanical Engineers
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• v.12 no.5
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• pp.984-991
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• 1988

Liquid column separation occurs when the valve on the pipeline is closed rapidly in an oil hydraulic system. In this case two-step pressure rise is sometimes observed in a comparatively short pipeline. In this study the two-step pressure rise phenomenon was investigated experimentally and theoretically. The experiments showed that maximum pressure values during two-step pressure rise might exceed extremely the values computed by the theory of rigid-liquid-column separation. So the two-step pressure rise phenomenon appears one of important factors of pipe strength design. From the theoretical considerations based on the experimental and numerical results, the mechanism of two-step pressure rise phenomenon could be explained clearly.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.38 no.9
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• pp.731-737
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• 2014

A vortex chamber is a simple device that separates compressed gas into a high-temperature stream and a low-temperature stream. It is increasing in popularity as a next-generation heat exchanger, but the flow physics associated with it is not yet well understood. In the present study, both experimental and numerical analyses were performed to investigate the temperature separation phenomenon inside the vortex chamber. Static pressures and temperatures were measured using high-sensitivity pressure transducers and thermocouples, respectively. Computational fluid dynamics was applied to simulate 3D unsteady compressible flows. The simulation results showed that the temperature separation is strongly dependent on the diameter of the vortex chamber and the supply pressure at the inlet ports, where the latter is closely related to the viscous work. The previous concept of a pressure gradient wave may not be a reasoning for temperature separation phenomenon inside the vortex chamber.

• Proceedings of the KSME Conference
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• 2003.04a
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• pp.1730-1735
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• 2003

The plume-induced shock wave is a complex phenomenon, consisting of plume-induced boundary layer separation, separated shear layer, multiple shock waves, and their interactions. The knowledge base of plume interference effect on powered missiles and flight vehicles is not yet adequate to get an overall insight of the flow physics. Computational studies are performed to better understand the flow physics of the plume-induced shock and separation particularly at high plume to exit pressure ratio. Test model configurations are a simplified missile model and two rounded and porous afterbodies to simulate moderately and highly underexpanded exhaust plumes at the transonic/supersonic speeds. The result shows that the rounded afterbody and porous wall attached at the missile base can alleviate the plume-induced shock wave phenomenon, and improve the control of the missile body.

• Journal of the Korean Home Economics Association
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• v.48 no.6
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• pp.9-16
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• 2010

The formative exaggeration phenomenon, which makes the plastic space, escaping from the form peculiar to the human body, is being developed into the more diversified and abstract structure. This study analyzed the form and shape of costumes with objective attitude through the use of an oppositional concept method, which Delong presented from the formative viewpoint. Delong's theory, which was presented in this study, can be said to be one index that analyzed the form and shape of costumes. The costumes of the Renaissance Era, in which formative exaggeration is remarkable, are determinate in that they are closed and static, and can be classified into part, planer separation, and flat. The costumes of the Baroque and Rococo Eras are divided into similar formative perspectives, and can be said to be open, whole, and integrated due to indeterminate and diverse decorations. Entering modern times, the formative-exaggeration phenomenon in costumes of the Romantic Era are characterized by closed, part, and planer separation similar to costumes of the Renaissance Era. However, in the aspect of sleeve design and decoration, the characteristics of determinate and indeterminate were considered.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.78-81
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• 2008

A numerical study of the unsteady flow in an over-expanded thrust optimized contour and compressed truncated perfect rocket nozzle is carried out in present paper. These rocket nozzles are subject to flow separation in transient phase at engine start-up and/or engine shut-down. The separation flow structures at different pressure ratios are observed. The start-up process exhibits two different shock structures such as FSS (Free Shock Separation) and RSS (Restricted Shock Separation). For a range of pressure ratios, hysteresis phenomenon occurs between these two separation patterns. A three-dimension compressible Navier-Stokes solver is used for the present study. One equation Spalart-Allmaras turbulence model is selected. The computed nozzle wall pressures show a good agreement with the experimental measurements. Present results have shown that present code can be used for the analysis of the transient flows in nozzle.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.05a
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• pp.45-48
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• 2003

The plume interference is a complex phenomenon, consisting of plume-induced boundary layer separation, separated shear layer, multiple shock waves, and their interactions. The base knowledge of plume interference effect on powered missiles and flight vehicles is not yet adequate to get an overall insight of the flow physics in plume-freestream flow field. Computational studies are performed to better understand the flow physics of the plume-induced shock and separation for Simple, Rounded, Porous-extension test model configurations. The present study simulates highly underexpanded exhaust plume effect on missile body at the transoni $c^ersonic speeds. In order to investigate the plume-induced separation phenomenon, Simple, Rounded and Porous-extension plate are attacked to the missile afterbody. The computational result shows that the rounded afterbody and the porous-extension wall attached at the missile base can alleviate the plume-induced shock wave and separation phenomenon and improve the control of the missile body.dy.

• Progress in Superconductivity and Cryogenics
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• v.18 no.1
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• pp.14-18
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• 2016

Organic compounds have a problem that the separation of structural isomer in the preparation process requires high energy consumption. This study proposes a new separation method of structural isomer using Magneto- Archimedes method. Firstly, the levitation height of 1, 6-DDA and 1, 10-DDA was respectively calculated by simulation of the forces acting on the particles under magnetic field, and it was indicated that they could be separated by the difference of levitation height. To confirm the phenomenon experimentally, white powders of 1, 6-DDA and 1, 10-DDA were formed into pellets, and were soaked in manganese chloride solution. Then the solution was put on the center of the cryostat of HTS bulk magnet (maximum magnetic flux density is 3T). As a result, it was confirmed that the separation of structural isomer by difference of levitation height could be possible.

• Journal of the Korean Society for Library and Information Science
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• v.23
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• pp.33-62
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• 1992

The purpose of this is to evaluate the contents through the anal us is of the merits and demerits, and its special quality of the Cutter-Sanborn Three-figure Author Table. table. The abstract of this study is as follows : With the results of the analysis of Cutter-Sanborn's Tabls, several advent-age were found in the area of enumerative-ordinal numbering system, mixed notation, and information retrieval. A defect is that each corporate author and serials and reference book's titles are difficult to be numbered, and there is serious diviation in percentages of the numbers assigned to each letter because each letter apportion rate was applied without any criteria. Such phenomenon decrease the effectiveness as author notation in several letters. The separation of headings are seriously unbalanced because the separation of heading is not consistent with actual publishing trends. This phenomenon made difficult individualization of materials in several letters.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.329-333
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• 2005

Total temperature distribution in high speed fee & wall jet regions was investigated using the total temperature probe. For the free jet, the distance of probe from the nozzle exit is changed in the range of 1, 2, 4 and 6 times o nozzle exit diameter. Energy separation phenomenon was observed on shear layer between jet and ambient. In wall jet region, impinging plate was fixed at Z/D=2 and total temperature distribution has been measured for various radial distance($R/D=1.25\sim2.0$). Energy separation phenomenon was found at wall jet boundary and near wall, and was compared with measured adiabatic wall temperature value.

• Journal of the Korean Society of Manufacturing Process Engineers
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• v.17 no.3
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• pp.59-64
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• 2018

In general, tracked combat vehicles require excellent output performance of a power unit system to drive on special terrains and in extreme environmental conditions. However, high temperature and pressure are readily applied to the coolant hose in the power unit of the vehicles during high-speed driving under extreme road and weather conditions. These driving conditions can cause the separation phenomenon of the coolant hose in the power unit and consequentially engine overheating during driving. Therefore, a newly designed decompression device for the coolant hose has been proposed and manufactured to solve these problems in the present study. To validate of the newly proposed decompression device, the input and output pressures were measured under the before- and after-improvement conditions using experimental methods for different engine RPMs. In addition, the pre-heater temperature was measured under both conditions. From the experimental results, we expect that the current investigation can help to improve the driving performance of tracked combat vehicles.