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AIC Computations Using Navier-Stokes Equations on Single Image Supercomputers For Design OptimizationA procedure to accurately generate AIC using the Navier-Stokes solver including grid deformation is presented. Preliminary results show good comparisons between experiment and computed flutter boundaries for a rectangular wing. A full wing body configuration of an orbital space plane is selected for demonstration on a large number of processors. In the final paper the AIC of full wing body configuration will be computed. The scalability of the procedure on supercomputer will be demonstrated.
Document ID
20040152047
Acquisition Source
Ames Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Guruswamy, Guru (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 7, 2013
Publication Date
July 27, 2004
Subject Category
Aircraft Design, Testing And Performance
Meeting Information
Meeting: 46th AIAA/ASME Structures, Structural Dynamics and Materials Conference
Location: Austin, TX
Country: United States
Start Date: April 11, 2005
End Date: April 15, 2005
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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