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Results of investigations on the 0.004-scale model 74-0 of the configuration 4 (modified) space shuttle vehicle orbiter in the NASA/MSFC 14-by-14-inch trisonic wind tunnel (oa131)The results of an oil flow boundary-layer visualization wind tunnel test of an 0.004-scale model of the Space Shuttle Vehicle Orbiter in the NASA/Marshall Space Flight Center 14-by-14-inch Trisonic Wind Tunnel are presented. The model was tested at Mach numbers from 0.60 through 2.75, at angles-of-attack from 0 through 25 degrees, and at unit Reynolds numbers from 5.0 to 7.0 million per foot. The test program involved still and motion picture photography of oil-paint flow patterns on the orbiter, during and immediately after tunnel flow, to determine areas of boundary layer separation and regions of potential auxiliary power unit exhaust recirculation during transonic and low supersonic re-entry flight.
Document ID
19750017927
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Nichols, M. E.
(Rockwell International Downey, Calif., United States)
Date Acquired
September 3, 2013
Publication Date
March 1, 1975
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NASA-CR-141521
DMS-DR-2232
Accession Number
75N25999
Funding Number(s)
CONTRACT_GRANT: NAS9-13247
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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