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Predictions of F-111 TACT aircraft buffet responseA summary is presented for the prediction method development and correlations of predicted response with flight test measurements. The prediction method was based on refinements to the method described by Cunningham. One improvement made use of direct time integration of the correlated fluctuating pressure data to obtain buffet excitation for the various modes of interest. Another improvement incorporated a hybrid technique for scaling measured wind tunnel damping data to full-scale for the modes of interest. A third improvement made use of the diagonalized form of the fully coupled equations of motion. Finally, a mechanism was described for explaining an apparent coupling between the aircraft wing torsion modes and shock induced trailing edge separation that led to very high wing motion on the aircraft that was not observed on the wind tunnel model.
Document ID
19910005022
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cunningham, Atlee M., Jr.
(General Dynamics Corp. Fort Worth, TX., United States)
Coe, Charles F.
(Coe Engineering, Inc., Los Altos CA., United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1990
Publication Information
Publication: AGARD, Aircraft Dynamic Loads Due to Flow Separation
Subject Category
Aircraft Stability And Control
Accession Number
91N14335
Funding Number(s)
CONTRACT_GRANT: NAS2-11420
Distribution Limits
Public
Copyright
Other
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