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Heat transfer investigation of Langley Research Center transition models at a Mach number of 8, volume 2The results are presented of a wind tunnel test program to determine aerodynamic heat transfer distributions on delta body and straight body transition models of the space shuttle. Heat transfer rates were determined by the phase-change paint technique on Stycast and RTV models using Tempilag as the surface temperature indicator. The nominal test conditions were: Mach 8, length Reynolds numbers of 5 million and 7.4 million, and angles of attack of 20, 40, and 60 deg. Model details, test conditions, and reduced heat transfer data are included. Data reduction of the phase-change paint photographs was performed by utilizing a new technique.
Document ID
19720015245
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Matthews, R. K. (ARO, Inc. New Orleans, LA, United States)
Martindale, W. R. (ARO, Inc. New Orleans, LA, United States)
Warmbrod, J. D. (Chrysler Corp.)
Johnson, C. B. (Chrysler Corp.)
Date Acquired
August 6, 2013
Publication Date
March 1, 1972
Subject Category
Space Vehicles
Report/Patent Number
NASA-CR-120045
DMS-DR-1224-VOL-2
Accession Number
72N22895
Funding Number(s)
CONTRACT_GRANT: NAS8-4016
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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