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Supersonic aerodynamic characteristics of a variable-geometry spacecraft designed for high hypersonic performanceAn investigation was made in the high Mach number test section of the Langley Unitary Plan wind tunnel on a variable-geometry high hypersonic performance spacecraft concept at Mach numbers from 2.30 to 4.63. The basic lifting body is designed for hypersonic lift-drag ratio near 3.0. The variable-geometry feature is a single-pivot two-position high wing which is deployed at subsonic speeds to improve vehicle landing characteristics. For the present investigation the wing was maintained in a stowed position, and the effects of horizontal stabilizer dihedral, elevon control effectiveness, and the addition of either a conventional single vertical tail or dorsal-fin-type vertical stabilizers on the longitudinal and lateral-directional stability and control characteristics were studied.
Document ID
19730007258
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Spencer, B., Jr. (NASA Langley Research Center Hampton, VA, United States)
Fournier, R. H. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
January 1, 1973
Subject Category
Aerodynamics
Report/Patent Number
L-8639
NASA-TM-X-2703
Accession Number
73N15985
Funding Number(s)
PROJECT: RTOP 502-37-01-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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