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Effects of the six engine air breathing propulsion system on space shuttle orbiter subsonic stability and control characteristicsExperimental aerodynamic investigations were conducted on a 0.0405 scale representation of the -89B space shuttle orbiter in the 7.75 x 11.00 foot low speed wind tunnel during the time period September 4 - 14, 1973. The primary test objective was to optimize the air breathing propulsion system nacelle cowl-inlet design and to determine the aerodynamic effects of this design on the orbiter stability and control characteristics. Nacelle cowl-inlet optimization was determined from total pressure - static pressure measurements obtained from pressure rakes located in the left hand nacelle pod at the engine face station. After the optimum cow-inlet design, consisting of a 7 deg cowl lip angle, short cowl, 7 deg short diverter, and a nacelle toe-in angle of 5 deg was selected, the aerodynamic effects of various locations of this design were investigated. The 3 pod - 6 Nacelle configuration was tested both underwing and overwing in three different longitudinal locations. Orbiter control effectiveness, both with and without Nacelles, was investigated at elevon deflections of 0 deg, -10 deg and +15 deg and at aileron deflections of 0 deg and +10 deg about 0 deg elevon.
Document ID
19740010396
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Mennell, R. C. (Rockwell Intern. Los Angeles, United States)
Soard, T. (Rockwell Intern. Los Angeles, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1974
Subject Category
Space Vehicles
Report/Patent Number
NASA-CR-134078
DMS-DR-2086
Accession Number
74N18509
Funding Number(s)
CONTRACT_GRANT: NAS9-13247
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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