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Effects of reaction control system jet simulation on the stability and control characteristics of a 0.015 scale space shuttle orbiter model tested in the Langley Research Center unitary plan wind tunnelAn experimental investigation was performed in the Langley Research Center Unitary Plan Wind Tunnel (Test 0A70) to obtain the detailed effects that RCS jet flow interactions with local orbiter flow field have on supersonic stability and control characteristics of the space shuttle orbiter. Six-component force data were obtained through an angle-of-attack range from 15 to 35 degrees at angles of sideslip of 0, +5, and -5 degrees. The test was conducted with yaw jet simulation at free-stream Mach numbers of 2.5 and 4.6, simulating SSV re-entry flight conditions at these Mach numbers. In addition to the basic force measurements, fuselage base pressures and pressures on the non-metric RCS pods were obtained.
Document ID
19740012434
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Daileda, J. J. (Rockwell Intern. Downey, Calif., United States)
Marroquin, J. (Rockwell Intern. Downey, Calif., United States)
Date Acquired
September 3, 2013
Publication Date
February 1, 1974
Subject Category
Space Vehicles
Report/Patent Number
NASA-CR-134070
DMS-DR-2073
Accession Number
74N20547
Funding Number(s)
CONTRACT_GRANT: NAS9-13247
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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