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Integration of Multifidelity Multidisciplinary Computer Codes for Design and Analysis of Supersonic AircraftThis paper documents the development of a conceptual level integrated process for design and analysis of efficient and environmentally acceptable supersonic aircraft. To overcome the technical challenges to achieve this goal, a conceptual design capability which provides users with the ability to examine the integrated solution between all disciplines and facilitates the application of multidiscipline design, analysis, and optimization on a scale greater than previously achieved, is needed. The described capability is both an interactive design environment as well as a high powered optimization system with a unique blend of low, mixed and high-fidelity engineering tools combined together in the software integration framework, ModelCenter. The various modules are described and capabilities of the system are demonstrated. The current limitations and proposed future enhancements are also discussed.
Document ID
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Geiselhart, Karl A.
(NASA Langley Research Center Hampton, VA, United States)
Ozoroski, Lori P.
(NASA Langley Research Center Hampton, VA, United States)
Fenbert, James W.
(Alliant Techsystems, Inc. Hampton, VA, United States)
Shields, Elwood W.
(Alliant Techsystems, Inc. Hampton, VA, United States)
Li, Wu
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 25, 2013
Publication Date
January 4, 2011
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA Paper 2011-0465
Meeting Information
Meeting: 49th AIAA Aerospace Sciences Meeting
Location: Orlando, FL
Country: United States
Start Date: January 4, 2011
End Date: January 7, 2011
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 984754.
Distribution Limits
Public Use Permitted.
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