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Aerodynamic characteristics at mach numbers from 2.5 to 3.5 of a canard bomber configuration designed for supersonic cruise flightResilts have been obtained from an investigation in the Langley Unitary Plan wind tunnel at Mach numbers from 2.5 to 3.5 of a canard-type configuration designed for supersonic cruise flight. Tests extended over an angle-of-attack range from about -4 deg to 11 deg and an angle-of-sideslip range from -4 deg to 6 deg. For the present tests, the results indicate that forebody deflection was an efficient means of providing a sizable positive pitching-moment shift with little or no increase in drag. The test configuration had a trimmed lift-drag ratio of approximately 6.0 at Mach numbers near 3.0 and at a Reynolds number of 2.52 X 10(exp 6). The configuration was both longitudinally and directionally stable. The lift-drag ratios are believed to be somewhat low in as much as the models used for the present tests had large-grain size transition strips fixed to the various surfaces and these strips added wave drag. Also, the model boundary-layer diverter is oversized with respect to a full-scale configuration and therefore contributes additional drag.
Document ID
19680068704
Acquisition Source
Headquarters
Document Type
Other - NACA Research Memorandum
Authors
Carmel, M. M. (NASA Langley Research Center Hampton, VA, United States)
Gregory, D. T. (NASA Langley Research Center Hampton, VA, United States)
Kelly, T. C. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 29, 2013
Publication Date
September 10, 1958
Publication Information
Publisher: NACA
Subject Category
Aerodynamics
Report/Patent Number
NACA-RM-L58G16
Accession Number
68N83515
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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