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F/A-18 1/9th scale model tail buffet measurementsWind tunnel tests were carried out on a 1/9th scale model of the F/A-18 at high angles of attack to investigate the characteristics of tail buffet due to bursting of the wing leading edge extension (LEX) vortices. The tests were carried out at the Aeronautical Research Laboratory low-speed wind tunnel facility and form part of a collaborative activity with NASA Ames Research Center, organized by The Technical Cooperative Program (TTCP). Information from the program will be used in the planning of similar collaborative tests, to be carried out at NASA Ames, on a full-scale aircraft. The program covered the measurement of unsteady pressures and fin vibration for cases with and without the wing LEX fences fitted. Fourier transform methods were used to analyze the unsteady data, and information on the spatial and temporal content of the vortex burst pressure field was obtained. Flow visualization of the vortex behavior was carried out using smoke and a laser light sheet technique.
Document ID
19910020835
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Martin, C. A. (Aeronautical Research Lab. Moffett Field, CA., United States)
Glaister, M. K. (Aeronautical Research Lab. Moffett Field, CA., United States)
Maclaren, L. D. (Aeronautical Research Lab. Moffett Field, CA., United States)
Meyn, L. A. (NASA Ames Research Center Moffett Field, CA., United States)
Ross, J. (NASA Ames Research Center Moffett Field, CA., United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1991
Subject Category
Aircraft Stability And Control
Report/Patent Number
ARL-FLIGHT-MECH-R-188
AR-006-149
AD-A242882
Accession Number
91N30149
Distribution Limits
Public
Copyright
Public Use Permitted.

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