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Body and canard effects on an attached-flow maneuver wing at Mach 1.62A wing-body-canard configuration was tested at a Mach number of 1.62 by using both a cambered and an uncambered wing. The cambered wing was designed to produce efficient high lift by using attached supercritical crossflow and was originally tested as an isolated wing. The uncambered wing has the same planform and essentially the same thickness distribution as the cambered wing. The experiment determined the effects of a body and canards on both wings. The experimental data showed that both the body and the canards influenced the wing pressure levels, but that the attached supercritical crossflow, which was achieved in the isolated cambered-wing test, was maintained in the presence of a body and canards. Tables of experimental pressure, force, and moment data are included, as well as photographs of oil flow patterns on the upper surface.
Document ID
19840010095
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Pittman, J. L. (NASA Langley Research Center Hampton, VA, United States)
Miller, D. S. (NASA Langley Research Center Hampton, VA, United States)
Mason, W. H. (Grumman Aerospace Corp. Bethpage, N.Y., United States)
Date Acquired
September 4, 2013
Publication Date
February 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.60:2249
L-15677
NASA-TP-2249
Accession Number
84N18163
Funding Number(s)
PROJECT: RTOP 505-43-23-03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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