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Heat transfer tests of an 0.006-scale thin-skin space shuttle model (41-OTS) in the Ames 3.5-foot HWT at M equals 5.3 (IH15)Data obtained from heat transfer tests of an 0.006-scale space shuttle vehicle in a 3.5-foot hypersonic wind tunnel are presented. The purpose of these tests was to parametrically investigate the ascent heating of the integrated vehicle. Configurations tested were complete for integrated vehicle, orbiter alone, external tank alone, and SRB alone. All configurations were tested with and without transition grit. Testing was conducted at a Mach number of 5.3, and at Reynolds numbers of 2 and 5 million per foot. The angle of attack range varied from 0 to minus 5 degress, execpt for SRB alone, which was tested from minus 5 to 90 degrees. Heat transfer data were obtained from 223 iron-constantan thermocouples attached to thin-skin stainless steel inserts.
Document ID
19750002915
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Walstad, D. G.
(Rockwell International Corp. Downey, Calif., United States)
Lockman, W. K.
(NASA Ames Research Center)
Date Acquired
September 3, 2013
Publication Date
October 1, 1974
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NASA-CR-134096
DMS-DR-2098
Accession Number
75N10987
Funding Number(s)
CONTRACT_GRANT: NAS9-13247
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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