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Effect of gaseous and solid simulated jet plumes on a 040A space shuttle launch configuration at Mach numbers from 1.6 to 2.2An experimental investigation was conducted in a 9- by 7-foot supersonic wind tunnel to determine the effect of plume-induced flow separation and aspiration effects due to operation of both the orbiter and the solid rocket motors on a 0.019-scale model of the launch configuration of the space shuttle vehicle. Longitudinal and lateral-directional stability data were obtained at Mach numbers of 1.6, 2.0, and 2.2 with and without the engines operating. The plumes exiting from the engines were simulated by a cold gas jet supplied by an auxiliary 200 atmosphere air supply system, and by solid body plume simulators. Comparisons of the aerodynamic effects produced by these two simulation procedures are presented. The data indicate that the parameters most significantly affected by the jet plumes are the pitching moment, the elevon control effectiveness, the axial force, and the orbiter wing loads.
Document ID
19740010397
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Lanfranco, M. J.
(Chrysler Corp. New Orleans, LA, United States)
Sparks, V. W.
(Chrysler Corp. New Orleans, LA, United States)
Kavanaugh, A. T.
(Chrysler Corp. New Orleans, LA, United States)
Date Acquired
September 3, 2013
Publication Date
December 1, 1973
Subject Category
Space Vehicles
Report/Patent Number
NASA-CR-128762
DMS-DR-2013
Accession Number
74N18510
Funding Number(s)
CONTRACT_GRANT: NAS9-13247
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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