Performance Benchmark for a Prismatic Flow Solver
Abstract
HPC Institute for Advanced Rotorcraft Modeling and Simulation (HI-ARMS) seeks the performance evaluation on various near-body/off-body spatial partitioning paradigm for the development of a computation engine for DoD's 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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 26, 2007
- Accession Number
- ADA482623
Entities
People
- Bharat K. Soni
- Yasushi Ito
Organizations
- University of Alabama