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Response Surface Modeling of Combined-Cycle Propulsion Components using Computational Fluid DynamicsThree examples of response surface modeling with CFD are presented for combined cycle propulsion components. The examples include a mixed-compression-inlet during hypersonic flight, a hydrogen-fueled scramjet combustor during hypersonic flight, and a ducted-rocket nozzle during all-rocket flight. Three different experimental strategies were examined, including full factorial, fractionated central-composite, and D-optimal with embedded Plackett-Burman designs. The response variables have been confined to integral data extracted from multidimensional CFD results. Careful attention to uncertainty assessment and modeling bias has been addressed. The importance of automating experimental setup and effectively communicating statistical results are emphasized.
Document ID
20020082924
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Steffen, C. J., Jr. (NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
September 7, 2013
Publication Date
March 1, 2002
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
AIAA Paper 2002-0542
E-13204
NASA/TM-2002-211379
NAS 1.15:211379
Meeting Information
Meeting: 40th Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 14, 2002
End Date: January 17, 2002
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
PROJECT: RTOP 708-90-63
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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