Parallel fluid dynamics computations in aerospace applications

S. K. Aliabadi*, T. E. Tezduyar

*この研究の対応する著者

研究成果: Article査読

74 被引用数 (Scopus)

抄録

Massively parallel finite element computations of the compressible Euler and Navier‐Stokes equations using parallel supercomputers are presented. The finite element formulations are based on the conservation variables and the streamline‐upwind/Petrov‐Galerkin (SUPG) stabilization method is used to prevent potential numerial oscillations due to dominant advection terms. These computations are based on both implicit and explicit methods and their parallel implementation assumes that the mesh is unstructured. The implicit computations are based on iterative strategies. Large‐scale 3D problems are solved using a matrix‐free iteration technique which reduces the memory requirements significantly. The flow problems we consider typically come from aerospace applications, including those in 3D and those involving moving boundaries interacting with boundary layers and shocks. Problems with fixed boundaries are solved using a semidiscrete formulation and the ones involving moving boundaries are solved using the deformable‐spatial‐domain/stabilized‐space‐time (DSD/SST) formulation.

本文言語English
ページ(範囲)783-805
ページ数23
ジャーナルInternational Journal for Numerical Methods in Fluids
21
10
DOI
出版ステータスPublished - 1995 11 30
外部発表はい

ASJC Scopus subject areas

  • 計算力学
  • 材料力学
  • 機械工学
  • コンピュータ サイエンスの応用
  • 応用数学

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