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Results of tests OA12 and IA9 in the Ames Research Center unitary plan wind tunnels on an 0.030-scale model of the space shuttle vehicle 2A to determine aerodynamic loads, volume 18Tests were conducted, during April and May 1973, on an 0.030-scale replica of the Space Shuttle Vehicle Configuration 2A. Aerodynamic loads data were obtained at Mach numbers from 0.6 to 3.5. The investigation included tests on the integrated (launch) configuration, and on the isolated orbiter (entry configuration). The integrated vehicle was tested at angles of attack and sideslip from -8 degrees to +8 degrees. The isolated orbiter was tested at angles of attack from -15 degrees to +40 degrees and angles of sideslip from -10 degrees to +10 degrees as dictated by trajectory considerations. The effect of orbiter/external tank incidence angle and deflected control surfaces on aerodynamic loads were also investigated.
Document ID
19740018213
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Spangler, R. H. (Rockwell Intern. Corp. Downey, Calif., United States)
Date Acquired
September 3, 2013
Publication Date
April 1, 1974
Subject Category
Space Vehicles
Report/Patent Number
DMS-DR-2032-VOL-18
NASA-CR-128794
Accession Number
74N26326
Funding Number(s)
CONTRACT_GRANT: NAS9-13247
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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