NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
A parallel finite-difference method for computational aerodynamicsA finite-difference scheme for solving complex three-dimensional aerodynamic flow on parallel-processing supercomputers is presented. The method consists of a basic flow solver with multigrid convergence acceleration, embedded grid refinements, and a zonal equation scheme. Multitasking and vectorization have been incorporated into the algorithm. Results obtained include multiprocessed flow simulations from the Cray X-MP and Cray-2. Speedups as high as 3.3 for the two-dimensional case and 3.5 for segments of the three-dimensional case have been achieved on the Cray-2. The entire solver attained a factor of 2.7 improvement over its unitasked version on the Cray-2. The performance of the parallel algorithm on each machine is analyzed.
Document ID
19900031280
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Swisshelm, Julie M.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Subject Category
Computer Programming And Software
Meeting Information
Meeting: International Conference on Finite Element Methods in Flow Problems
Location: Huntsville, AL
Country: United States
Start Date: April 3, 1989
End Date: April 7, 1989
Accession Number
90A18335
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available