Performance Benchmark for a Prismatic Flow Solver
Final rept. 13 Mar-12 Dec 2006
ALABAMA UNIV IN BIRMINGHAM
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HPC Institute for Advanced Rotorcraft Modeling and Simulation HI-ARMS seeks the performance evaluation on various near-bodyoff-body spatial partitioning paradigm for the development of a computation engine for DoDs mission-critical design and analysis tasks. The purpose of this project is to benchmark the prismatic flow solver derived from the Tohoku University Aerodynamic Simulation TAS flow solver with a common test problem. The TAS code is an unstructured, implicit, compressible flow solver developed by Nakahashi et al. The full Reynolds-averaged Navier-Stokes RANS equations that retain the unsteady form are solved by a finite volume cell-vertex scheme. The control volumes are non-overlapping dual cells constructed around each node. The Harten-Lax-van Leer-Einfeldt-Wada HLLEW Reimann solver is used for the numerical flux computations. The Lower-Upper-Symmetric Gauss-Seidel LU-SGS implicit method is used for time integration to reduce the computational time. A one-equation turbulence model by Goldberg and Ramakrishnan and the Spalart-Allmaras model are implemented to treat turbulent boundary layers. A grid reordering method is implemented for the cell-vertex scheme implementation for three-dimensional hybrid grids for the LU-SGS method. The deliverables are used as the basis for measuring the attributes of the prismatic flow solver and its potential to meet long-term HI-ARMS objectives and program requirements.
- Fluid Mechanics
- Computer Systems Management and Standards