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Heating Augmentation for Short Hypersonic ProtuberancesComputational aeroheating analyses of the Space Shuttle Orbiter plug repair models are validated against data collected in the Calspan University of Buffalo Research Center (CUBRC) 48 inch shock tunnel. The comparison shows that the average difference between computed heat transfer results and the data is about 9.5%. Using CFD and Wind Tunnel (WT) data, an empirical correlation for estimating heating augmentation on short hypersonic protuberances (k/delta less than 0.3) is proposed. This proposed correlation is compared with several computed flight simulation cases and good agreement is achieved. Accordingly, this correlation is proposed for further investigation on other short hypersonic protuberances for estimating heating augmentation.
Document ID
20080024047
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Mazaheri, Ali R. (NASA Langley Research Center Hampton, VA, United States)
Wood, William A. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 24, 2013
Publication Date
June 23, 2008
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
Paper 4255
Meeting Information
Meeting: 40th AIAA Thermophysics Conference
Location: Seattle, WA
Country: United States
Start Date: June 23, 2008
End Date: June 26, 2008
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 37781606030308
CONTRACT_GRANT: NNL06AC49T
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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