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Interference effects of aft reaction-control yaw jets on the aerodynamic characteristics of a space shuttle orbiter model at supersonic speedsA wind tunnel investigation of the interference effects of aft reaction control system yaw jet plumes on a 0.0125 scale Space Shuttle orbiter model was conducted at Mach numbers from 2.50 to 4.50. Test variables included model angle of attack, model angle of sideslip, jet to free stream mass flow ratio, and number and position of operating jets. The aft reaction control jet plume creates a blockage above and behind the wing on the side in which the jet exhausts and results in flow separation on the wing upper surface and fuselage side. Positive pitching moment and side force increments and negative yawing moment and rolling moment increments due to the flow separations are incurred for left side firing jets, primarily at angles of attack above 10 deg. The yawing moment interference increments are favorable and result in a small jet thrust amplification. As a result of this investigation, the aft reaction control system was certified for operation at supersonic Mach numbers prior to the first flight of the space transportation system (STS-1).
Document ID
19830017390
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Covell, P. F. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
June 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-84645
NAS 1.15:84645
L-15576
Accession Number
83N25661
Funding Number(s)
PROJECT: RTOP 505-43-33-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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