Computation of a transonic finite wing flow using Hanbit-1 computer

Author

Kim, M.H. ; Cho, S.M. ; Park, S.O.

Author_Institution

Dept. of Aerosp. Eng., Korea Adv. Inst. of Sci. & Technol., Seoul, South Korea

fYear

1997

fDate

28 Apr-2 May 1997

Firstpage

85

Lastpage

88

Abstract

This paper reports the results of a parallel computation of a transonic flow past a 3D wing using the Hanbit-1 computer, a hypercube parallel computer developed at KAIST (Korea Advanced Institute of Science and Technology). Two different numerical schemes, one a lower-upper symmetric Gauss-Seidel (LU-SGS) method and the other a Runge-Kutta time-stepping scheme, were used. The performance of the Hanbit-1 was assessed based on the present parallel computation with domain decomposition

Keywords

Runge-Kutta methods; aerodynamics; aerospace computing; aerospace simulation; external flows; flow simulation; hypercube networks; iterative methods; parallel machines; parallel programming; performance evaluation; transonic flow; 3D wing; Hanbit-1 computer; Runge-Kutta time-stepping scheme; domain decomposition; hypercube parallel computer; lower-upper symmetric Gauss-Seidel method; numerical schemes; parallel computation; performance assessment; transonic finite wing flow; Acceleration; Computational fluid dynamics; Computational modeling; Concurrent computing; Differential equations; Hypercubes; Integral equations; Jacobian matrices; Operating systems; Parallel processing;

fLanguage

English

Publisher

ieee

Conference_Titel

High Performance Computing on the Information Superhighway, 1997. HPC Asia '97

Conference_Location

Seoul

Print_ISBN

0-8186-7901-8

Type

conf

DOI

10.1109/HPC.1997.592127

Filename

592127