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Wing-Body Aeroelasticity Using Finite-Difference Fluid/Finite-Element Structural Equations on Parallel ComputersIn recent years significant advances have been made for parallel computers in both hardware and software. Now parallel computers have become viable tools in computational mechanics. Many application codes developed on conventional computers have been modified to benefit from parallel computers. Significant speedups in some areas have been achieved by parallel computations. For single-discipline use of both fluid dynamics and structural dynamics, computations have been made on wing-body configurations using parallel computers. However, only a limited amount of work has been completed in combining these two disciplines for multidisciplinary applications. The prime reason is the increased level of complication associated with a multidisciplinary approach. In this work, procedures to compute aeroelasticity on parallel computers using direct coupling of fluid and structural equations will be investigated for wing-body configurations. The parallel computer selected for computations is an Intel iPSC/860 computer which is a distributed-memory, multiple-instruction, multiple data (MIMD) computer with 128 processors. In this study, the computational efficiency issues of parallel integration of both fluid and structural equations will be investigated in detail. The fluid and structural domains will be modeled using finite-difference and finite-element approaches, respectively. Results from the parallel computer will be compared with those from the conventional computers using a single processor. This study will provide an efficient computational tool for the aeroelastic analysis of wing-body structures on MIMD type parallel computers.
Document ID
20010048902
Document Type
Preprint (Draft being sent to journal)
Authors
Byun, Chansup (NASA Ames Research Center Moffett Field, CA United States)
Guruswamy, Guru P. (NASA Ames Research Center Moffett Field, CA United States)
Kutler, Paul
Date Acquired
August 20, 2013
Publication Date
January 1, 1994
Subject Category
Aerodynamics
Funding Number(s)
PROJECT: RTOP 509-10-00
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.