http://chineseinput.net/에서 pinyin(병음)방식으로 중국어를 변환할 수 있습니다.
변환된 중국어를 복사하여 사용하시면 됩니다.
성춘호(Chun-ho Sung),권장혁(Jang Hyuk Kwon),최윤호(Yoon-Ho Choi),이승수(Seung-Soo Lee) 한국전산유체공학회 2001 한국전산유체공학회 학술대회논문집 Vol.2001 No.-
A multigrid DADI method for low Mach number preconditioning method is presented. The eigenvalues of governing equations are modified by A low Mach number preconditioner developed by Choi & Merkle, and it results in an accurate solution and fast convergence in the low Mach number region. The convergence of numerical method is further accelerated by multigrid method. The efficient and accuracy of present method is shown by comparison with conventional solution method for tbe compressible flows.
성춘호(Chun-ho Sung),조금원(Kum Won Cho),박형우(Hyungwoo Park),이상산(Sangsan Lee),김대희(Dae-Hee Kim),권장혁(Jang Hyuk Kwon) 한국전산유체공학회 2002 한국전산유체공학회 학술대회논문집 Vol.2002 No.-
The grid technology is believed to be the next generation research tool for both computational and experimental scientists. With advanced network technologies and middleware, geographically distributed facilities can be tightly connected to provided a huge amount of resources or remote accessibility. In this paper, an overview of grid technology will be introduced with an emphasis in application to computational fluid dynamics. The computational fluid dynamics, which involves solution of partial differential equations, is basically limited by the computing power, With the grid technology, virtually unlimited resources are provided. The schematic structure of middleware and grid environment, as well as some preliminary results are presented.
3차원 압축성 유동 해석을 위한 효율적인 다중 격자 DADI 기법
박수형(Soo-Hyung Park),성춘호(Chun-ho Sung),권장혁(Jang Hyuk Kwon) 한국전산유체공학회 1998 한국전산유체공학회 학술대회논문집 Vol.1998 No.-
An efficient 3-dimensional compressible solver is developed using the second-order upwind TVD scheme and the multigrid diagonalized ADI method. The multigrid method is improved so that the present DADI algorithm obtains better convergence rates. Results are computed on Cray C90 computer for transonic unsaperated flows past ONERA-M6 wing to demonstrate the accuracy and efficiency. The results show good agreement with experimental data. A reduction of four orders of residual for 3-dimensional transonic flow is obtained about 99 seconds.