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Analysis of heat-transfer measurements from 2 AEDC wind tunnels on the Shuttle external tankPrevious aerodynamic heating tests have been conducted in the AEDC/VKF Supersonic Wind Tunnel (A) to aid in defining the design thermal environment for the space shuttle external tank. The quality of these data has been under discussion because of the effects of low tunnel enthalpy and slow model injection rates. Recently the AEDC/VKF Hypersonic Wind Tunnel (C) has been modified to provide a Mach 4 capability that has significantly higher tunnel enthalpy with more rapid model injection rates. Tests were conducted in Tunnel C at Mach 4 to obtain data on the external tank for comparison with Tunnel A results. Data were obtained on a 0.0175 scale model of the Space Shuttle Integrated Vehicle at Re/ft = 4 x 10 to the 6th power with the tunnel stagnation temperature varying from 740 to 1440 R. Model attitude varied from an angle of attack of -5 to 5 deg and an angle of sideslip of -3 to 3 deg. One set of data was obtained in Tunnel C at Re/ft = 6.9 x 10 to the 6th for comparison with flight data. Data comparisons between the two tunnels for numerous regions on the external tank are given.
Document ID
19850019951
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Nutt, K. W. (Calspan Field Services, Inc. Arnold AFS, TN, United States)
Date Acquired
September 5, 2013
Publication Date
October 1, 1984
Publication Information
Publisher: AEDC
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
AEDC-TR-84-03
NASA-CR-171470
NAS 1.26:171470
Accession Number
85N28263
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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