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An investigation of the increase in vortex induced rolling moment associated with landing gear wakeFlight tests were conducted to verify the results found in ground base facilities of the effect of span lift load variation as well as the vortex attentuation of the high energy jet engine exhaust through proper thrust programming. During these flight tests a large increase in vortex strength was experienced as a result of extending the landing gear. Tests in the Langley Vortex Research Facility indicate that the wake produced by the landing gear may possibly form an aerodynamic endplate or reflection plane at the inboard edge of each inboard flap which increases the effective aspect ratio of the flap and thereby increases the strength of the flap outer edge vortex.
Document ID
19760003950
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Patterson, J. C., Jr. (NASA Langley Research Center Hampton, VA, United States)
Jordan, F. L., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
November 1, 1975
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-X-72786
Accession Number
76N11038
Funding Number(s)
PROJECT: RTOP 514-52-01-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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