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Experimental assessment of a computer program used in Space Shuttle orbiter entry heating analysisA high temperature reusable surface insulation (HRSI) tile taken from the Space Shuttle orbiter was subjected to a nominal heating rate of 60 kW/sq m in the laboratory. The surface temperature response to this heating was measured and used as input to a computer program which computed the applied heating rate. The program is part of a software system that is used to infer convective heating rates to the orbiter thermal protection system during entry. The measured and computed heating rates are compared. Results confirm the applicability of this program to the determination of flight heat transfer rates from flight measured surface temperature data.
Document ID
19830008397
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Wells, W. L.
(NASA Langley Research Center Hampton, VA, United States)
Hudgins, J.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1983
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NAS 1.15:84572
L-15515
NASA-TM-84572
Accession Number
83N16668
Funding Number(s)
PROJECT: RTOP 506-51-33-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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