PARALLEL FLUID-DYNAMICS COMPUTATIONS IN AEROSPACE APPLICATIONS

Massively parallel finite element computations of the compressible Eul er and Navier-Stokes equations using parallel supercomputers are prese nted. The finite element formulations are based on the conservation va riables and the streamline-upwind/Petrov-Galerkin (SUPG) stabilization method is used to prevent potential numerial oscillations due to domi nant advection terms. These computations are based on both implicit an d 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 it eration technique which reduces the memory requirements significantly. The flow problems we consider typically come from aerospace applicati ons, including those in 3D and those involving moving boundaries inter acting with boundary layers and shocks. Problems with fixed boundaries are solved using a semidiscrete formulation and the ones involving mo ving boundaries are solved using the deformable-spatial-domain/stabili zed-space-time (DSD/SST) formulation.