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Experimental aerodynamic heating to simulated shuttle tilesThe heat transfer to simulated shuttle thermal protection system tiles was investigated experimentally using a highly instrumented metallic thin wall tile arranged with other metal tiles in a staggered tile array. Cold-wall heating rate data for laminar and turbulent flow were obtained in the Langley 8-foot high temperature tunnel at a nominal Mach number of 7, a nominal total temperature of 3300 R, free-stream unit Reynolds number from 3.4 x 10 to the 5th power to 2.2 x 10 to the 6th power per foot, and free-stream dynamic pressure of 1.8 psia to 9.1 psia. Experimental data are presented to illustrate the effects of flow angularity and gap width on both local peak heating and overall heating loads.
Document ID
19830014276
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Avery, D. E. (NASA Langley Research Center Hampton, VA, United States)
Kerr, P. A. (NASA Langley Research Center Hampton, VA, United States)
Wieting, A. R. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
April 1, 1983
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
AIAA PAPER 83-1536
NAS 1.15:84654
NASA-TM-84654
Meeting Information
Meeting: AIAA Thermophys. Conf.
Location: Montreal
Start Date: June 1, 1983
End Date: June 3, 1983
Accession Number
83N22547
Funding Number(s)
PROJECT: RTOP 506-51-23-03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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