• Title/Summary/Keyword: Parallelized Multi Grid Method

Search Result 3, Processing Time 0.017 seconds

Parallel Preconditioner for the Domain Decomposition Method of the Discretized Navier-Stokes Equation (이산화된 Navier-Stokes 방정식의 영역분할법을 위한 병렬 예조건화)

  • Choi, Hyoung-Gwon;Yoo, Jung-Yul;Kang, Sung-Woo
    • Transactions of the Korean Society of Mechanical Engineers B
    • /
    • v.27 no.6
    • /
    • pp.753-765
    • /
    • 2003
  • A finite element code for the numerical solution of the Navier-Stokes equation is parallelized by vertex-oriented domain decomposition. To accelerate the convergence of iterative solvers like conjugate gradient method, parallel block ILU, iterative block ILU, and distributed ILU methods are tested as parallel preconditioners. The effectiveness of the algorithms has been investigated when P1P1 finite element discretization is used for the parallel solution of the Navier-Stokes equation. Two-dimensional and three-dimensional Laplace equations are calculated to estimate the speedup of the preconditioners. Calculation domain is partitioned by one- and multi-dimensional partitioning methods in structured grid and by METIS library in unstructured grid. For the domain-decomposed parallel computation of the Navier-Stokes equation, we have solved three-dimensional lid-driven cavity and natural convection problems in a cube as benchmark problems using a parallelized fractional 4-step finite element method. The speedup for each parallel preconditioning method is to be compared using upto 64 processors.

Transonic Wing Flutter Analysis Using a Parallel Euler Solver (병렬화된 오일러 코드를 이용한 3차원 날개의 천음속 플러터 해석)

  • Kwon, Hyuk-Jun;Park, Soo-Hyung;Kim, Kyung-Seok;Kim, Jong-Yun;Lee, In;Kwon, Jang-Hyuk
    • Journal of the Korean Society for Aeronautical & Space Sciences
    • /
    • v.33 no.10
    • /
    • pp.10-16
    • /
    • 2005
  • In this paper, a three-dimensional Euler aeroelastic analysis program is developed with a second-order staggered algorithm to reduce the lagging errors between the fluid and structural solvers. In the unsteady aerodynamic analysis, a dual-time stepping method based on the diagonalized-ADI algorithm is adopted to improve the time accuracy and a parallelized multi-grid method is used to save the computing time. The aeroelastic analyses of AGARD 445.6 wing model have been performed to verify the Euler aeroelastic analysis code. The analysis results are compared with the experimental data and other computational results. The results show comparatively good correlation when they are compared with other references.