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Results of two tests in the MSFC 14 by 14-inch trisonic wind tunnel, FA 27 (TWT-655) and FA 28 (TWT-656)Wind tunnel tests were conducted in a 14- inch wind tunnel with a 0.004 scale model of the space shuttle launch vehicle in order to (1) determine the cause and possible aerodynamic alterations required to eliminate the Orbiter rolling moment couple; (2) determine configuration alterations to alleviate the forward Orbiter external tank loads; and (3) provide data to verify previous data.
Document ID
19800012796
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Braddock, W. F. (Lockheed Missiles and Space Co. Huntsville, AL, United States)
Date Acquired
September 4, 2013
Publication Date
December 1, 1979
Subject Category
Aerodynamics
Report/Patent Number
LMSC-HREC-TR-D697767
NASA-CR-161427
Accession Number
80N21281
Funding Number(s)
CONTRACT_GRANT: NAS8-32530
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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