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Transonic wind tunnel tests of a .015 scale space shuttle orbiter model, volume 2Transonic wind tunnel tests were run on a 0.015 scale model of the Space Shuttle Orbiter Vehicle in an eight-foot tunnel during August 1975. The purpose of the program was to obtain basic shuttle aerodynamic data through a full range of elevon and aileron deflections, verification of data obtained at other facilities, and effects of Reynolds numbers. The second part of a discussion of test procedures and results in both tabular and graphical form were presented. Tests were performed at Mach numbers from 0.35 to 1.20, and at Reynolds numbers from 3.5 million to 8.2 million per foot. The angle of attack was varied from -2 to +20 degrees at sideslip angles of -2, 0, +2 degrees. Sideslip was varied from -6 to +8 degrees at constant angles of attack from 0 to +20 degrees. Various aileron and ailevon settings were tested for various angles of attack.
Document ID
19760004127
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Struzynski, N. A.
(Calspan Corp. Buffalo, NY, United States)
Date Acquired
September 3, 2013
Publication Date
August 1, 1975
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NASA-CR-144547
AA-4018-W-13-VOL-2
Accession Number
76N11215
Funding Number(s)
CONTRACT_GRANT: NAS9-14752
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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