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Canard-wing lift interference related to maneuvering aircraft at subsonic speedsAn investigation was conducted at Mach numbers of 0.7 and 0.9 to determine the lift interference effect of canard location on wing planforms typical of maneuvering fighter configurations. The canard had an exposed area of 16.0 percent of the wing reference area and was located in the plane of the wing or in a position 18.5 percent of the wing mean geometric chord above the wing plane. In addition, the canard could be located at two longitudinal stations. Two different wing planforms were tested: one with a leading-edge sweep angle of 60 deg and the other with a leading-edge sweep angle of 44 deg. The results indicated that although downwash from the canard reduced the wing lift at angles of attack up to approximately 16 deg, the total lift was substantially greater with the canard on than with the canard off. At angles of attack above 16 deg, the canard delayed the wing stall. Changing canard deflection had essentially no effect on the total lift, since the additional lift generated by the canard deflection was lost on the wing due to an increased downwash at the wing from the canard.
Document ID
19740003706
Document Type
Technical Memorandum (TM)
Authors
Gloss, B. B. (NASA Langley Research Center Hampton, VA, United States)
Mckinney, L. W. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
December 1, 1973
Subject Category
AERODYNAMICS
Report/Patent Number
NASA-TM-X-2897
L-9096
Funding Number(s)
PROJECT: RTOP 760-67-01-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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