• Proceedings of the IEEK Conference
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• 2000.06b
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• pp.246-249
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• 2000

In this paper, we describe an automated extraction program that transforms a mask layout into an approximated equivalent circuit information suitable for circuit simulation, and that extract the geometric parameters of stacked MOSFETs and the distributed RCs of layout blocks. To extract equivalent circuit from mask layout, we propose new block disassembly technique capable of accurate computations of distributed RCs at branch point, using vectorized edges which represent the outline of an individual polygon.

• Bulletin of the Korean Mathematical Society
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• v.52 no.4
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• pp.1213-1223
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• 2015

We examine a family of isolated complex surface singularities whose exceptional curves consist of two complex curves with high genera intersecting transversally. Topological data of smoothings of these singularities are determined. We use these computations to construct symplectic 4-manifolds by replacing neighborhoods of the exceptional curves with smoothings of the singularities.

• Proceedings of the Korean Society of Broadcast Engineers Conference
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• 1996.06a
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• pp.209-212
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• 1996

In this paper, we propose to re-size images using an oblique projection operator instead of the orthogonal one in order to obtain faster, simpler, and more general algorithms. The main advantage is that it becomes perfectly feasible to use higher order models(e.g., splines of degree n 3). We develop the theoretical background and present a simple and practical implementation procedure that uses B-splines. Experiments show that the proposed algorithm consistently outperforms the standard interpolation method and that it essentially provides the same performance as the optimal procedure (least squares solution) with considerably less computations.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.04a
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• pp.14-14
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• 2000

One of the most important aerodynamic performance characteristics for projectiles is the total drag which can be typically divided into three components, pressure drag (excluding the base), viscous skin friction drag, and base drag. In a range of supersonic flight speeds the base drag is a major contributor to the total drag and can be as much as 50%∼70% of the total drag, depending on the afterbody configuration of projectiles. It is of especial importance to minimize this part of. the drag.

• Journal of the Korean Mathematical Society
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• v.34 no.4
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• pp.841-857
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• 1997

We present analysis and some computational methods for boundary optimal and feedback control problems for Navier-Stokes equations. We use one example to illustrate our methodology and ideas which are applicable to general control problems for Navier-Stokes equations. First, we discuss the existence of optimal solutions and derive an optimality system of equations from which an optimal solution may be computed. Then we present a gradient type iterative method. Finally, we present some numerical results.

• Proceedings of the IEEK Conference
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• 1998.10a
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• pp.363-366
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• 1998

High frequency scattered fields by a double impedence wedge are computed. In the procedure of the computation, arbitrary impedence faces and wedge angles are considered. The diffraction coefficients for the single, double and triple diffraction mechanism are founded. The second-order and third-order diffracted fields are approximated via the extended spectral ray method and the modified Pauli-Clemmow method of the steepest descent. The maliuzhinets function which is very difficult to obtain accurate value is approximated by the Volakis's asymtotic expression. Numerical computations are performed for the various wedge angles and surface impedence values.

• 한국전산유체공학회:학술대회논문집
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• 2000.10a
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• pp.39-45
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• 2000

Hypersonic analysis on the KSR-III payload configuration has been performed using an axisymmetric Navier-Stokes code. A numerical code based on the Harten and Yee's upwind TVD scheme with simplified curve fits in the equilibrium chemically reacting air was developed. The carbuncle phenomenon on detached shock in front of the payload is controlled by using pressure gradients to tune the dissipation. Equilibrium chemically reacting computations for reentry flight conditions of Mach no. 10.2, 8, 4.9 are presented and compared with the results of calorically perfect gas.

• 한국전산유체공학회:학술대회논문집
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• 2000.10a
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• pp.170-175
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• 2000

Parametric studies are performed of the factors influencing the afterbody drag. To display the effect of differing afterbody shapes, several ogive boattails with combinations of the base area and the angle of boattail end are computed using axisymmetric Navier-Stokes equations with central differencing and a DADI scheme. And Chien's $\kappa-\epsilon$ model is employed used for computations of turbulent flows around the base region. The effects of base area, boattail angle and jet on/off are illustrated on afterbody drag at transonic speed.

• 제어로봇시스템학회:학술대회논문집
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• 1991.10b
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• pp.1617-1622
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• 1991

Plane sweep is a general method in computational geometry. There are many efficient theoretical algorithms designed using plane sweep technique. However, their practical implementations are still suffering from the topological inconsistencies resulting from the numerical errors in geometric computations with finite-precision arithmetic. In this paper, we suggest new implementation techniques for the plane sweep algorithms to resolve the topological inconsistencies and construct the planar object boundaries from given input curve segments.

• Journal of ILASS-Korea
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• v.4 no.2
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• pp.10-18
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• 1999

The droplet/wall impingement processes in the diesel-like environment are numerically modeled. In order to evaluate the predictive capability of the droplet/wall impingement model developed in this study, computations are carried out for two ambient temperature conditions. Numerical results indicate that the present droplet/wall impingement model reasonably well predicts the basic features of the impinging spray dynamics.