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Optimization on a Network-based Parallel Computer System for Supersonic Laminar Wing DesignA set of Computational Fluid Dynamics (CFD) routines and flow transition prediction tools are integrated into a network based parallel numerical optimization routine. Through this optimization routine, the design of a 2-D airfoil and an infinitely swept wing will be studied in order to advance the design cycle capability of supersonic laminar flow wings. The goal of advancing supersonic laminar flow wing design is achieved by wisely choosing the design variables used in the optimization routine. The design variables are represented by the theory of Fourier series and potential theory. These theories, combined with the parallel CFD flow routines and flow transition prediction tools, provide a design space for a global optimal point to be searched. Finally, the parallel optimization routine enables gradient evaluations to be performed in a fast and parallel fashion.
Document ID
20020005092
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Garcia, Joseph A.
(NASA Ames Research Center Moffett Field, CA United States)
Cheung, Samson
(MCAT Inst. Moffett Field, CA United States)
Holst, Terry L.
Date Acquired
August 20, 2013
Publication Date
January 1, 1995
Subject Category
Aircraft Design, Testing And Performance
Meeting Information
Meeting: NASA Computational Aerosciences (CAS) Workshop
Location: Moffett Field, CA
Country: United States
Start Date: March 7, 1995
End Date: March 9, 1995
Sponsors: NASA Ames Research Center
Funding Number(s)
PROJECT: RTOP 509-10-00
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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