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Flow Visualization Study of a 1/48-Scale AFTI/F111 Model to Investigate Horizontal Tail Flow DisturbancesDuring flight testing of the AFTI/F111 aircraft, horizontal tail buffet was observed. Flutter analysis ruled out any aeroelastic instability, so a water-tunnel flow visualization study was conducted to investigate possible flow disturbances on the horizontal tail which might cause buffet. For this study, a 1/48-scale model was used. Four different wing cambers and one horizontal tail setting were tested between 0 and 20 deg angle of attack. These wing cambers corresponded to the following leading training edge deflections: 0/2, 10/10, 10/2, and 0/10. Flow visualization results in the form of still photographs are presented for each of the four wing cambers between 8 and 12 deg angle of attack. In general, the horizontal tail experiences flow disturbances which become more pronounced with angle of attack or wing trailing-edge deflection.
Document ID
19910014815
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Bjarke, Lisa J.
(NASA Hugh L. Dryden Flight Research Facility Edwards, CA, United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
H-1547
NASA-TM-101698
NAS 1.15:101698
Accession Number
91N24128
Funding Number(s)
PROJECT: RTOP 533-02-11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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