• The Korean Journal of Applied Statistics
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• v.23 no.5
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• pp.909-921
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• 2010

Cross-wave regression imputation and carry-over imputation method are generally used in the analysis of panel data with missing values. Recently it is known that the BLS non-response adjust method has good statistical properties. In this paper we show that the BLS method can be considered as an imputation method with a similar formula of a ratio-estimator. In addition, we show that the carry-over imputation and BLS imputation are approximately the same under the assumption that data follow a non-stationary process with drift. Small simulation studies and real data analysis are performed. For the real data analysis, a monthly labor statistic (2007) is used.

• Proceedings of the KSME Conference
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• 2005.11a
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• pp.59.1-59.1
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• 2005

• Proceedings of the Korean Operations and Management Science Society Conference
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• 1993.04a
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• pp.424-436
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• 1993

패널내 추계적 성분들의 공분산 관계(variance-covariance structure)를 이용한 ML 추정법을 항상소득가설(PIH)의 검증에 적용하였다. Hall & Mishkin의 모형을 기초로 분기별 이분산성(heteroscedasticity)을 고려한 모형의 추정결과 전체 소비변동 중 약 11%가 과도민감성에 의한 것으로 나타났다.

• Journal of the Society of Naval Architects of Korea
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• v.47 no.3
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• pp.398-409
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• 2010

This paper considers the numerical computation of added resistance on ships in the presence of incident waves. As a method of solution, a higher-order Rankine panel method is applied in time domain. The added resistance is evaluated by integrating the second-order pressure on the body surface. Computational results are validated by comparing with experimental data and other computational results on a hemi-sphere, a barge, Wigley hull models, and Series 60 hull, showing very fair agreements. The study is extended to the comparison between Neumann-Kelvin and double-body linearization approaches, and their differences are discussed.

• Journal of Ocean Engineering and Technology
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• v.14 no.3
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• pp.41-45
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• 2000

In solving the unsteady potential flow problem of the ship in waves with the panel method, in general one can consider the basic flow as the free stream or double body solution. For the double body solution, the body boundary condition has the 2nd derivatives of the velocity potential. Low order panel methods are known to suffer from the significant error in the 2nd derivatives computed at the body surface. This paper analyzes the numerical error in the 2nd derivatives for a 2-D cylinder and a 3-D sphere problem, and an extrapolation method to obtain the correct derivatives on the body surface is suggested.

• Journal of Advanced Marine Engineering and Technology
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• v.17 no.2
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• pp.44-51
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• 1993

Here is represented a vortex panel method to evaluate the performance characteristics of the 2-dimensional turbomachinery with circular arc blades or logarithmic blades. The present method is characterized by distributing small consecutive panels of linearly varing vortex strength satisfying boundary condition at control points and Kutta condition at trailing edge. To confirm the reliability of the present method, experimental result of a 2-D pump impeller of six circular arc blades is compared with the calculated one. As an application of the present method, figures are presented in series showing velocity and pressure distribution between blades.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.5
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• pp.375-380
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• 2007

The nonlinear aerodynamic analysis of wing with control surface is performed using the frequency-domain panel method. To take into consideration the nonlinear aerodynamic characteristics of wing an iterative decambering approach is introduced. The iterative decambering approach uses the known aerodynamic characteristics of airfoil to calculate the aerodynamic characteristics of wing. The multi-dimensional Newton iteration is used to account for the coupling between the different sections of wing. The present method is verified by showing that it produces results that are in good agreement with experiments. The present method will be useful for the analysis of aircraft in the conceptual design because the present method can calculate promptly the nonlinear aerodynamic characteristics of wing with a few computing resources.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.7
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• pp.9-17
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• 2005

The wake patterns and thrust characteristics of dual flapping airfoils in a biplane configuration are investigated using an unsteady panel method. To trace complicated wake shapes behind airfoils, a core addition scheme, a vortex core model, and the fourth order Runge-Kutta convection scheme are employed. Present results are verified by comparing them with flow visualization, exact solution and published computed results. The thickness and camber of thick airfoils has an effect of decreasing thrust. The airfoils produce maximum thrust when the phase angles between plunging and pitching motions are both 90 and 120 degrees. Thrust increases as the plunge velocity is increased, which is also found as the pitch amplitude is stepped up. Thrust decreases when the distance between the airfoils is less than 0.6c.

• Journal of Ocean Engineering and Technology
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• v.22 no.5
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• pp.25-30
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• 2008

A B-spline based high order panel method was developed for the motion of bodies in an ideal fluid, either of infinite extent or with a free boundarysurface. In this method, both the geometry and the potential are represented by the B-spline, which guarantees more accurate results than most potential based low order methods. In the present work, we applied this B-spline based high order method to the radiation problem of floating bodies. The boundary condition on the free surface was satisfied by adopting a Kelvin-type Green function and irregular frequencies were removed by placing additional control points on the free surface surrounding the body. The numerical results were validated by comparison with existing numerical and experimental results.

• Journal of the Society of Naval Architects of Korea
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• v.37 no.3
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• pp.27-36
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• 2000

A higher order panel method based on B-spline representation for both the geometry and the velocity potential is developed for the solution of the flow around two-dimensional lifting bodies. Unlike Lee/Kerwin, who placed multiple control points on each panel and solved the overdetermined system of equation by the least square approach, the present method places only as many number of control points as required by the unknowns of the problem. Especially, a null pressure jump Kutta condition at the trailing edge is found to be effective in stabilizing the solution process and in predicting the correct solution. The new approach, is validated to be accurate through comparison with the analytic solution for a 2-D airfoil and to be less time-consuming due to fewer number of panels required than that used in Lee/Kerwin.