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Transonic single-mode flutter and buffet of a low aspect ratio wing having a subsonic airfoil shapeTransonic flutter and buffet results obtained from wind-tunnel tests of a low aspect ratio semispan wing model are presented. The tests were conducted to investigate potential transonic aeroelastic problems of vehicles having subsonic airfoil sections. The model employed NACA 00XX-64 airfoil sections in the streamwise direction and had a 14 deg leading edge sweep angle. Aspect ratio, and average thickness were 4.0, 0.35, and 8 percent, respectively. The model was tested at Mach numbers from 0.6 to 0.95 at angles of attack from 0 deg to 15 deg. Two zero lift flutter conditions were found that involved essentially single normal mode vibrations. With boundary layer trips on the model, flutter occurred in a narrow Mach number range centered at about Mach 0.90. The frequency and motion of this flutter were like that of the first normal mode vibration. With the trips removed flutter occurred at a slightly high Mach number but in a mode strongly resembling that of the second normal mode.
Document ID
19740006518
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Erickson, L. L. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1974
Subject Category
Structural Mechanics
Report/Patent Number
A-4966
NASA-TN-D-7346
Accession Number
74N14631
Funding Number(s)
PROJECT: RTOP 502-32-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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