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Performance of LI-1542 reusable surface insulation system in a hypersonic streamThe thermal and structural performance of a large panel of LI-1542 reusable surface insulation tiles was determined by a series of cyclic heating tests using radiant lamps and aerothemal tests in the Langley 8-foot high-temperature structures tunnel. Aerothermal tests were conducted at a free-stream Mach number of 6.6, a total temperature of 1830 K, Reynolds numbers of 2.0 and 4,900,000 per meter, and dynamic pressures of 29 and 65 kPa. The results suggest that pressure gradients in gaps and flow impingement on the header walls at the end of longitudinal gaps are sources for increased gap heating. Temperatures higher than surface radiation equilibrium temperature were measured deep in gaps and at the header walls. Also, the damage tolerance of the LI-1542 tiles appears to be very high. Tile edge erosion rate was slow; could not be tolerated in a shuttle application. Tiles soaked with water and subjected to rapid depressurization and aerodynamic heating showed no visible evidence of damage.
Document ID
19740015359
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Hunt, L. R. (NASA Langley Research Center Hampton, VA, United States)
Bohon, H. L. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
April 1, 1974
Subject Category
Thermodynamics And Combustion
Report/Patent Number
NASA-TM-X-71955
Accession Number
74N23472
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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