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정석영(S.Y. Jung),윤성준(S.J. Yoon) 한국전산유체공학회 2008 한국전산유체공학회 학술대회논문집 Vol.2008 No.-
For simulation of a wing unfolding motion for the various aerodynamic conditions, equation governing unfolding motion and moments applying to the unfolding wing were modelled. Aerodynamic roll moment consists of the static roll moment and the damping moment, which were obtained through wind tunnel tests and numerical analyses respectively. Panel method was used to compute the roll damping coefficient with twisted wing, whose deflection angle was equivalent to angle of attack due to the deployment motion. Roll damping coefficient is a function of angle of attack, sideslip angle, and deployment angle but not of angular velocity of deployment. Simulation with aerodynamic damping model gave more similar deployment time compared to wing deployment test results.
허진영(J.Y. Huh),김규홍(K. Kim),정석영(S.Y. Jung) 한국전산유체공학회 2013 한국전산유체공학회 학술대회논문집 Vol.2013 No.5
The purpose of this study is to develop numerical analysis algorithm, which is being able to analyze the compressible flow by Meshless (or Gridless) method. This paper includes Meshless Method on 2-D steady inviscid compressible flow and numerical analysis results of it. The Meshless Method has two aspects. :1) Automatic point generation technique, 2) Numerical analysis scheme. The method applies to an analysis of flow around cylinder depending on a variety of flow velocities. And then it is conducted comparative analysis by a program which is based on Finite Volume Method (FVM) for confirmation of the efficiency, accuracy and convergence.
2차원 압축성 유동 해석을 위한 강건한 무격자 해석기법 개발
허진영(J.Y. Huh),이재상(J.S. Rhee),김규홍(K.H. Kim),정석영(S.Y. Jung) 한국전산유체공학회 2014 한국전산유체공학회지 Vol.19 No.3
The purpose of this study is to develop a new Meshless Method to solve 2-D compressible flow problems numerically. This paper includes a revised Least Square method that improves robustness compared with its original version by removing excessive numerical oscillation which occurs when points are randomly distributed. Numerical analyses of hypersonic flow over a blunt body were carried out using the method, then robustness, accuracy and convergence of their results were compared with those obtained from the original method.