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Effects of the air breathing propulsion system on space shuttle orbiter subsonic stability and control characteristics (OA71A)Experimental aerodynamic investigations were conducted on an 0.0405 scale representation of the -89B (2A) Space Shuttle Orbiter in a 7.75 x 11.00 ft low speed wind tunnel during the time period from July 27, 1973 to August 3, 1973. The primary test objective was to investigate the aerodynamic effects of engine nacelle grouping and location on the orbiter ferry mission configuration. Five nacelles were tested, both individually mounted as well as mounted in a podded configuration, at the baseline position and moved 45.0 in. aft (full scale). Orbiter control effectiveness, both with and without nacelles, was recorded at elevon deflections of 0 deg, 5 deg, 10 deg, -10 deg and -20 deg and aileron deflections, about 0 deg elevon, of 0 deg, 5 deg, 10 deg, and 15 deg. The model was sting mounted on a 2.5 inch diameter internal strain gage balance entering through the base region. The nominal angle of attack range was -4 deg or = alpha or = 30 deg. Yaw polars were recorded over the beta range of -10 deg or = beta or = at fixed angles of attack of 0 deg and 10 deg.
Document ID
19740005471
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Mennell, R. C. (Rockwell Intern. Downey, Calif., United States)
Date Acquired
September 3, 2013
Publication Date
November 1, 1973
Subject Category
Space Vehicles
Report/Patent Number
NASA-CR-128797
DMS-DR-2068
Accession Number
74N13584
Funding Number(s)
CONTRACT_GRANT: NAS9-13247
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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