• Journal of Drive and Control
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• v.14 no.1
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• pp.14-22
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• 2017

Flow force is the additional unbalanced force acting on the valve spool by fluid flow, excluding the static pressure force that is offset on the spool land wall at the same magnitude. When designing the valve spool, it is assumed that the same average value of static pressure is applied to the inlet and outlet spool land wall in one chamber. However, the high velocity of the fluid flow by the inlet or outlet metering orifice creates unbalanced pressure distribution and generates additional force in the opposite direction to that of the solenoid attraction force. This flow force has a negative effect on the control performance of the EPPR valve, which needs to develop uniform output pressure along the entire spool control range. In this study, we developed a 3D model of the EPPR valve and conducted flow force characteristic analysis using CFD S/W (ANSYS FLUENT). The alleviated flow force model was derived by adjusting the design parameters of the spool notch.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2010.04a
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• pp.345-346
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• 2010

본 연구에서는 모형실험 및 수치계산에 의해 정수중 부선 주위의 유통해석을 실시하였으며, 이를 통하여 객관적이고 정량적으로 부선의 저항추진 성능을 파악할 수 있었다. 먼저 희류수조에서 모형실험을 실시한 후, 실험에서 얻어진 데이터와의 비교를 통한 CFD의 유효성을 검증하고, 다른 형태의 예부선 선박 주위의 유동장 계산에 적용시켜 해결할 수 있는 가능성을 확인 하였다. 부선의 선수 형상에 의하여 저속일 때 25% 정도의 저항이 차이나는 현상을 모형실험을 통하여 파악할 수 있었으며, 유효마력은 7kts부터 급격히 증가하므로 적재상태별 경제적인 운항속력을 선정하여 효율적인 예부선 업무를 수행해야 할 것으로 판단된다.

• Aerospace Engineering and Technology
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• v.7 no.2
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• pp.151-156
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• 2008

Numerical analyses of two-stage turbopump turbines were conducted. One of the candidates for the 1st rotor was selected based on the result of the numerical investigation. Besides, the effects of the stator height on the turbine performance were studied. Finally, the performance of the entire two-stage turbine was predicted by numerical calculation. The result showed that the two-stage turbine produces more specific power than a one-stage turbine.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.32 no.1
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• pp.62-69
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• 2008

A post-processing program based on the OOP(Object-Oriented Programming) concept has been developed for flow visualization of the flow analysis code(PowerCFD) using unstructured cell-centered method. User-friendly GUI(GTaphic User Interface) has been built on the base of MFC(Microsoft Foundation Class). The program is organized as modules by classes including those based on VTK(Visualization ToolKit)-library, and these classes are made to function through inheritance and cooperation which is an important and valuable OOP concept. The major functions of this post-processor program are introduced and demonstrated, which include mesh plot, contour plot, vector plot, surface plots, cut plot, clip plot, xy-plot and streamline plot as well as view manipulation (translation, rotation, scaling etc).

• 유체기계공업학회:학술대회논문집
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• 2006.08a
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• pp.415-421
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• 2006

The unsteady flow calculation around the proprotor of Smart UAV was conducted. Using the flight scenario of SUAV which composed of hover, transition, and airplane mode, the aerodynamic analysis of proprotor were performed for the variation of collective pitch, rpm, forward speed, and tilt angle. The unsteady compressible Navier-Stokes equations were used for the calculation and the dynamic overset grid technique was applied for the rotating proprotor. The aerodynamic performance of proprotor calculated in this way were validated by comparing with the performance data obtained from the blade element momentum method.

• 한국전산유체공학회:학술대회논문집
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• 1998.11a
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• pp.42-47
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• 1998

The pressure-based methods are very popular in CFD because it requires less computer core memory compared to other coupled or density-based solvers. Currently structured-mesh methodology based on pressure-based algorithm is quite mature to apply to the practical problems. The unstructured mesh method needs much more computer memory than the structured-mesh method. However the pressure-based method utilizing the sequential approach does not require very large memory used for unstructured-mesh density-based solvers. The present study has developed the unstructured grid pressure-based method. Cell-centered finite volume method was selected due to robustness for imposing various boundary conditions and easy implementation of higher-order upwind scheme. The predictive capability of present method has validated against several benchmark problems.

• Journal of computational fluids engineering
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• v.9 no.4
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• pp.13-19
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• 2004

Flow distribution of a mid-size vehicle in engine room was investigated numerically to analyze the flow performance of given design cases in a front body of the mid-size vehicle. The data analyzed are the mass flow rate at the upper and lower openings, in the radiator, and the degree of non-uniformity of the velocity field at the inlet of the radiator. It is presented that the shape of the front end and the presence of the undercover greatly affect the flow fields, therefore, the flow performance.

• 한국전산유체공학회:학술대회논문집
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• 2007.04a
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• pp.8-13
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• 2007

Unsteady flow simulation for the tiltrotor Smart UAV configuration was performed to investigate the powered rotor wake effect on aerodynamic characteristics. Calculations were performed to simulate various flow conditions based on different flight modes including hover, conversion and cruise. Three-dimensional compressible Navier-Stokes equation code were used for flow calculation and Chimera grid technique overlapping individually generated grids was employed. A dynamic grid method was adopted in simulation of the rotating blades. Flow calculations were also conducted for the un-powered case. Aerodynamic interaction between the rotor and airframe was investigated comparing three data sets from the un-powered, powered, and isolated rotor cases.

• Proceeding of EDISON Challenge
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• 2014.03a
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• pp.521-526
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• 2014

현대에 이르러 초경량 무인 비행기에 대한 많은 연구가 진행되고 있다. 이러한 비행체는 저레이놀즈수 영역에서 사용되는 특성으로 인해, 경계층 내에서 박리현상과 난류영역으로의 천이 등과 같은 여러 복합적인 현상을 발생시킴으로써 비행체의 공력특성에 큰 영향을 미친다. Bumpy Airfoil은 저레이놀즈수 유동에서의 이와 같은 문제를 해결하기 위해 제안된 익형이다. 따라서 본 논문은 전산열유체해석 프로그램인 EDISON_전산열유체를 이용하여 Bumpy Airfoil 형상에 대한 공력특성을 연구하였고, 발생하는 양항비를 원 익형과 비교하였다. 비압축성 조건 내에서, 공력 성능 향상을 위한 Bumpy Airfoil의 형상 변수로 Bump 개수와 높이를 선정하여 받음각에 따른 유동장을 분석하고 양항비를 수치해석 및 고찰하였다.

• Proceedings of the KSME Conference
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• 2008.11b
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• pp.2612-2615
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• 2008

Diaphragm seals have great effects on the performance of large power-generation steam turbines. Hence, it is important to decrease the leakage flow through the diaphragm seals and understand the flow characteristics within the diaphragm seals. In this study, numerical analysis was carried-out with the seals of large one-body type diaphragms developed by a domestic company. CFX, which is a commercial CFD code, was used to analyze the performance and flow characteristics of the diaphragm seals for three difference clearance cases. The results of numerical analysis show variations in the performance and flow characteristics according to the changes of labyrinth seal clearance.