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Aerodynamic characteristics of a fixed arrow-wing supersonic cruise aircraft at Mach numbers of 2.30, 2.70, and 2.95Tests were conducted in the Langley Unitary Plan wind tunnel at Mach numbers of 2.30. 2.70, and 2.95 to determine the performance, static stability, and control characteristics of a model of a fixed-wing supersonic cruise aircraft with a design Mach Number of 2.70 (SCAT 15-F-9898). The configuration had a 74 deg swept warped wing with a reflexed trailing edge and four engine nacelles mounted below the reflexed portion of the wing. A number of variations in the basic configuration were investigated; they included the effect of wing leading edge radius, the effect of various model components, and the effect of model control deflections.
Document ID
19780024107
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Morris, O. A.
(NASA Langley Research Center Hampton, VA, United States)
Fuller, D. E.
(NASA Langley Research Center Hampton, VA, United States)
Watson, C. B.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
August 1, 1978
Subject Category
Aerodynamics
Report/Patent Number
L-12249
NASA-TM-78706
Accession Number
78N32050
Funding Number(s)
PROJECT: RTOP 505-11-13-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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