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Space Shuttle orbiter entry heating and TPS response: STS-1 predictions and flight dataAerothermodynamic development flight test data from the first orbital flight test of the Space Transportation System (STS) transmitted after entry blackout is given. Engineering predictions of boundary layer transition and numerical simulations of the orbiter flow field were confirmed. The data tended to substantiate preflight predictions of surface catalysis phenomena. The thermal response of the thermal protection system was as expected. The only exception is that internal free convection was found to be significant in limiting the peak temperature of the structure in areas which do not have internal insulation.
Document ID
19820015618
Document Type
Conference Paper
Authors
Ried, R. C. (NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Goodrich, W. D. (NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Li, C. P. (NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Scott, C. D. (NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Derry, S. M. (NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Maraia, R. J. (NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1982
Publication Information
Publication: NASA. Langley Research Center Computational Aspects of Heat Transfer in Struct.
Subject Category
FLUID MECHANICS AND HEAT TRANSFER
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19820015599Analytic PrimaryComputational Aspects of Heat Transfer in Structures