• 한국전산유체공학회지
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• 제17권1호
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• pp.94-100
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• 2012

In this paper, the cavitating flows around a hydrofoil have been numerically investigated by using a 2-d multi-phase RANS flow solver based on pseudo-compressibility and a homogeneous mixture model on unstructured meshes. For this purpose, a vertex-centered finite-volume method was utilized in conjunction with 2nd-order Roe's FDS to discretize the inviscid fluxes. The viscous fluxes were computed based on central differencing. The Spalart-Allmaras one equation model was employed for the closure of turbulence. A dual-time stepping method and the Gauss-Seidel iteration were used for unsteady time integration. The phase change rate between the liquid and vapor phases was determined by Merkle's cavitation model based on the difference between local and vapor pressure. Steady state calculations were made for the modified NACA66 hydrofoil at several flow conditions. Good agreements were obtained between the present results and the experiment for the pressure coefficient on a hydrofoil surface. Additional calculation was made for cloud cavitation around the hydrofoil. The observation of the vapor structure, such as cavity size and shape, was made, and the flow characteristics around the cavity were analyzed. Good agreements were obtained between the present results and the experiment for the frequency and the Strouhal number of cavity oscillation.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 추계학술대회논문집B
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• pp.523-528
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• 2001

There are many difficult problems in analyzing the flow characteristics in a high voltage circuit breaker such as shock wave and complex geometries, which may be either static or in relative motion. Although a variety of mesh generation techniques are now available, the generation of meshes around complicated, multicomponent geometries like a gas circuit breaker is still a tedious and difficult task for the computational fluid dynamics. This paper presents the computational method for analyzing the compressible flow fields in a high voltage gas circuit breaker using the Cartesian cut-cell method based on the CFD-CAD integration, which can achieve the accurate representation of the geometry designed by a CAD tools. The technique is frequently satisfied, and it will be almost universally so in the future, as the CFD-CAD traffic increases.

• 한국분무공학회지
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• 제5권1호
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• pp.13-22
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• 2000

The present study has numerically analyzed the vaporization characteristics of fuel droplets in the high temperature convective flow field. The axisymmetric governing equations for mass, momentum, energy, and species are solved by an iterative and implicite unstructured finite-volume method. The moving boundary due to vaporization is handled by the deformable unstructured grid technique. The pressure-velocity coupling in the density-variable flows is treated by the SIMPLEC algorithm. In terms of the matrix solver, Bi-CGSTAB is employed for the numerically efficient and stable convergence. The n-decane is used as a liquid fuel and the initial droplet temperature is 300K. Computations are performed for the nonevaporating and evaporating droplets with the relative interphase velocity(25m/s). The unsteady vaporization process has been simulated up to the nondimensional time, 25. Numerical results indicate that the mathematical model developed in this study succesfully simulates the main features of the droplet vaporization process in the convective environment.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2011년 춘계학술대회논문집
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• pp.447-452
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• 2011

Propeller shall have high efficiency and improved aerodynamic characteristics to get the thru5t to fly at high speed for the Regional turboprop aircraft. That is way Clark-Y airfoil which is used to conventional turboprop aircraft propeller is selected as a blade airfoil. Adkins method is used for aerodynamic design and performance analysis with respect to the propeller design point. Adkins method is based on the vortex-blade element theory which design the propeller to satisfy the condition for minimum energy loss. propeller geometry is generated by varying chord length and pitch angle at design point of Regional turboprop aircraft. The propeller design results indicate that is evaluated to be properly constructed, through analysis of propeller aerodynamic characteristics using the Meshless method and MRF, SM method.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2004년도 춘계학술대회
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• pp.1382-1387
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• 2004

From the viewpoint of a macro state, there is no thermal boundary resistance (TBR) at an interface if both surfaces at an interface are perfectly contacted. However, recent molecular dynamics (MD) studies reported that there still exists the TDR at the interface in an ideal epitaxial superlttice. Our previous studies suggested the model to predict the TBR not only quantitatively also qualitatively in superlattices. The suggested model was based on the classical theory of a wave reflection, and provided highly satisfactory results for an engineering purpose. However, it was not the complete model because our previous model was derived by considering only the effects from a mass ratio and a potential ratio of two species. The interaction of two species presented by the Lennard-Jones (L-J) potential is governed by the mutual ratio of the masses, the potential well depths, and the diameters. In this study, we performed the preliminary simulations to investigate the effect resulting from the diameter ratio of two species for the completion of our model and confirmed that it was also a ruling factor to the TBR at an interface in superlattices.

• 한국자기학회지
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• 제18권5호
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• pp.190-194
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• 2008

FePd 합금박막을 스퍼터링법으로 초격자 박막의 형태로 제작하고 기판온도, 조성변화에 따른 미세구조 및 자기적 특성을 분석하였다. FePd 합금박막의 규칙화를 위한 열처리 온도를 FePt의 열처리 온도에 비해 $150^{\circ}C$ 낮추는데 성공하였다. 또한 FePd 규칙화 합금 박막은 화학양론적 조성일 때 장범위 규칙도는 가장 높은 값을 가졌으며(Fe조성 50 at.%, S = 0.79), 자기이방성 에너지는 Fe 조성이 약간 낮은 조성에서(Fe조성 48 at.%, $K_U=1.6{\times}10^7\;erg/cm^3$) 가장 높은 값을 나타내었다. 이것은 FePd 합금박막의 조성이 장범위 규칙도와 수직자기이방성에 직접적으로 영향을 미친다는 것을 나타낸다.

• 한국세라믹학회지
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• 제39권12호
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• pp.1158-1163
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• 2002

2차 비선형 광특성을 유도하기 위한 UV 폴링용 Ge와 B가 첨가된 광민감성 광섬유를 제조하였다. 248 nm KrF 엑시머 레이저 조사에 의하여 수소처리 없이 장주기 격자를 형성할 수 있었다. 116 mJ/$cm^2$의 펄스 에너지와 10 Hz의 조사 빈도로 1분간 광민감성 광섬유에 레이저를 조사할 경우 -4 dB의 큰 band rejection 특성을 얻을 수 있었다. 제조된 광섬유의 광민감성은 장주기 격자쌍 방법을 이용하여 측정하였으며, 8.67 kJ/$cm^2$의 fluence로 KrF 엑시머 레이저를 조사할 경우 3.3${\times}10^{-3}$의 큰 코어 굴절률 변화를 얻었다. 또한 UV 폴링 시에 광섬유 코어에 고전압을 쉽게 인가할 수 있는 H자 형상의 광섬유를 인출조건의 최적호를 통하여 제조하였다.

• 대한조선학회논문집
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• 제33권2호
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• pp.56-64
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• 1996

균일 분포 횡하중이 작용하는 격자형 구조물의 극한 해석법의 개발에 대한 이전의 연구(참고문헌 1과 5)를 검증해 보았고, 붕괴 이론에 있어서 면내력의 영향을 고찰 하였다. 논문의 주된 내용은 최소 중량과 최소 비용을 갖는 격자형 구조물의 최적설계법을 개발하였고, Pareto 해석법을 적용하여 다목적 함수를 갖는 구조물에서 최적 절충해를 구하는 최적화 기법을 소개하였다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2010년 춘계학술대회논문집
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• pp.335-340
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• 2010

In this paper development of an automatic grid generation program for flow field calculation around 3D wing is described and its application is also introduced. The program is developed by using JAVA programming language and a graphic library, JOGL, and it can be usee either as an application program on a local computer or as a applet in the network environment. Currently, The program provides NACA series 4-digit airfoils as the wing cross-section shape and it offers a non-complicated GUI program which can easily generate structured grids for wings based on user's parameter input. Grid generated by the program can be selected as one of two types; O-type and C-type. In this research advancing layer method(ALM) augmented by elliptic smoothing method is used for the FLUENT. It is shown that by using current program high-quality structured grids around 3D wings can be easily generated, and typical grid generation results and flow solutions are demonstrated. Study on effects of geometric parameters on flow field is also tried by changing major wing parameters such as incidence angle type of wing-tip and sweepback angle.

• 전력전자학회:학술대회논문집
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• 전력전자학회 2004년도 전력전자학술대회 논문집(2)
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• pp.878-882
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• 2004

Position controls are very important in semiconductor manufacturing devices, machine tools precision measuring instruments, etc. In this paper, a novel encoder of digital and analog hybrid type is proposed. It is shown that from this experiment a high-resolution angle measurement device can be designed by a low cost incremental encoder.