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Experimental transonic flutter characteristics of supersonic cruise configurationsThe flutter characteristics of a generic arrow-wing supersonic transport configuration are studied. The wing configuration has a 3 percent biconvex airfoil and a leading-edge sweep of 73 deg out to a cranked tip with a 60 deg leading-edge sweep. The ground vibration tests and flutter test procedure are described. The effects of flutter on engine nacelles, fuel loading, wing-mounted vertical fin, wing angle-of-attack, and wing tip mass and stiffness distributions are analyzed. The data reveal that engine nacelles reduce the transonic flutter dynamic pressure by 25-30 percent; fuel loadings decrease dynamic pressures by 25 percent; 4-6 deg wing angles-of-attack cause steep transonic boundaries; and 5-10 percent changes in flutter dynamic pressures are the result of the wing-mounted vertical fin and wing-tip mass and stiffness distributions.
Document ID
19900042314
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Durham, Michael H.
(NASA Langley Research Center Hampton, VA, United States)
Cole, Stanley R.
(NASA Langley Research Center Hampton, VA, United States)
Cazier, F. W., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Keller, Donald F.
(NASA Langley Research Center Hampton, VA, United States)
Parker, Ellen C.
(Lockheed Engineering and Sciences Co. Hampton, VA, United States)
Wilkie, W. Keats
(NASA Langley Research Center; U.S. Army, Army Aviation Systems Command, Hampton VA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1990
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 90-0979
Meeting Information
Meeting: AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Location: Long Beach, CA
Country: United States
Start Date: April 2, 1990
End Date: April 4, 1990
Accession Number
90A29369
Distribution Limits
Public
Copyright
Other

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