• Journal of Advanced Marine Engineering and Technology
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• v.18 no.3
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• pp.94-101
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• 1994

To develope the new simulator for the analysis of fluid flow information, the influence of various convective difference schemes were evaluated. General curvilinear coordinate system with nonorthogonal grids was adopted for the successful analysis of various complex geometries. Computation results show that if we can not obtain full grid numbers within available computational environment, we need to use higher order finite difference schemes to keep the prediction accuracy.

• Journal of Korean Society of Coastal and Ocean Engineers
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• v.17 no.3
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• pp.158-165
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• 2005

In order to analyze incompressible two-phase flow, Level Set method was applied on pseudo-compressibility formulation. Level Set function is defined as a signed distance function from the phase interface, and gives the information of the each phase location and the geometric data to the flow. In this study, Level Set function transport equation was coupled with flow conservation equations, and owing to pseudo-compressibility technique we could solve the resultant vector equation iteratively. Two-phase flow analysis code was developed on general curvilinear coordinate, and numerical tests of bubble dynamics and surging wave problems demonstrate its capability successfully.

• Proceedings of the Korea Water Resources Association Conference
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• 2009.05a
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• pp.555-559
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• 2009

난류응력은 순간속도성분을 시간평균성분과 편차성분의 합으로 보고 Navier-Stokes 방정식으로부터 Reynolds 방정식을 유도할 때 나타나게 된다. Reynolds 방정식으로부터 수심 적분된 천수방정식을 유도하는 과정에서 시간 평균된 유속성분을 수심 적분된 유속성분과 편차성분의 합으로 본다면, 분산응력 (dispersion stress)이라고 하는 추가적인 새로운 항이 잔류하게 된다. 점성응력, 난류응력, 그리고 분산응력을 통칭하여 유효응력 (effective stress)이라고 한다. 일반적으로 수심에 비해 수로 폭이 넓은 개수로에서는 유효응력이 흐름특성의 수치 근사해에 큰 영향을 미치지 못한다고 가정하여 2차원 수심적분 모형에서 유효응력을 생략하기도 한다. 또한 유효응력을 적용하더라도, 점성응력이 난류응력에 비해 무시할 만큼 작다고 가정하여 난류응력만을 적용하며, 분산응력은 무시된다. 하지만 만곡부에서는 원심력과 편수위로 인한 횡방향 압력의 불균형이 발생하기 때문에, 만곡부의 이차류가 발생되며, 유속의 연직방향 분포도 일정하지 않게 된다. 따라서 본 연구의 목적은 만곡부의 이차류 특성을 수심적분 2차원 모형에 반영하기 위해 분산응력을 고려한 모형의 개발 및 검증이다. 불규칙한 모의영역을 원활히 나타낼 수 있도록 곡선좌표계를 사용하는 여타 모형들과 달리 유한유소법을 이용하여 수치해를 구하며, 따라서 x, y 좌표축을 사용하는 데카르트 좌표계를 사용하여 지배방정식을 나타낸다. 분산응력의 유 무에 따른 수치결과를 Rozovskii의 $180^{\circ}$ 만곡수로 실내실험 자료와 비교하여 개발 모형을 검증한다.

• Journal of the Society of Naval Architects of Korea
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• v.29 no.3
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• pp.59-70
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• 1992

A Finite volume method for the computation of the two-dimensional, incompressible, steady, laminar Navier-Stokes equation is developed using a non-staggered grid system in a general curvilinear coordinate. The numerical pressure fluctuations, usually encountered when the non-staggered grid system is used, is suppressed by the momentum interpolation method. Flows around a NACA0012 foil section have been computed by the present method and the results show good agreements with other experimental and numerical ones.

• Journal of the Society of Naval Architects of Korea
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• v.36 no.1
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• pp.61-69
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• 1999

To promote the usability of CFD techniques for the basic hull form design, a hull surface mesh generating program, based on given station offsets and centerline profile, is developed. The new method employs non-uniform parametric splines with predetermined waterline end-shapes of natural spline, normal spline, ellipse, parabola hyperbola, and their combinations. Generated hull surface meshes can be utilized for potential panel method immediately and can be also used as a boundary grid surface for 3-D field grid system. Mesh topology chosen to represent hull surface can be transformed into a rectangle, which he1ps the flow solvers to transform surface meshes for the nonlinear free surface condition or to define the turbulence quantities. To prove the applicability, a container ship with bow and stem bulb is chosen, and the procedures generating hull surface meshes are described.

• Journal of Biomedical Engineering Research
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• v.24 no.3
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• pp.183-192
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• 2003

A transformation methode of the chromaticity coordinates was proposed to calibrate the measured data obtained by a urine analysis system which implemented in our previous study. Generally. the reacted color of a reagent strip by urine analysis system often exhibit the color distortions due to nonlinear characteristics of the various devices that is the optic module mechanism. hardware, and surround circumstance. A color correction method for minimizing the color distortion play a few role in maintaining high accuracy and reproduction of the urine analysis system. In this work, we used the compensation method such as the shading correction, the characteristic curve extraction of RGB color by means of third order spline interpolation, and linear transformation using a reference color. In addition, 1931 CIE XYZ color space was used to compensate the color of the measured data by a standard reference system as colorimeter. A compensation matrix was obtained so that the output values of the urine analysis system is nearly equal to that of a standard reference system for identical color sample. Color correction obtained by a urine analysis system which implemented in our previous study exhibited a good color accuracy when it was compared with the reference data. Observed result from an experiments on ten items or a urinalysis strip that color difference or between two urine analysis system was 1.28.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.11
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• pp.1055-1065
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• 2009

In this study, stability analysis of boundary layers on airfoils is performed by using parabolized stability equations(PSE). Boundary layer edge conditions are obtained by compressible inviscid flow calculations. Mean velocity and temperature profiles of the laminar boundary layer are obtained by solving compressible boundary layer equations in generalized curvilinear coordinates with fourth order accuracy in the wall normal direction. Laminar mean flow profiles are used as input data for PSE to investigate growth rates of disturbances and stability characteristics. For the cases of boundary layer on NACA0012 and HSNLF(1)-0213 airfoils at Mach number 0.5, growth rates with respect to disturbance frequencies and profiles of disturbance amplitude are investigated. The effect of angle of attack on stability characteristics are examined at both upper and lower surfaces. The neutral stability curves, effect of Mach number and effect of airfoil section shapes are also analyzed.