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Flutter analysis of a transport wing using XTRAN3SAs part of the continuing process of evaluating and validating the XTRAN3S unsteady transonic aerodynamic computer program, the code has been applied to the flutter analysis of a transport type wing. The configuration analyzed was an aspect ratio 8 wing with a taper ratio of 0.4, a quarter chord sweep of 20 degrees and a NACA 65A-012 airfoil section. The analytical results compare well with the experimental flutter boundary and exhibit the classical 'transonic dip'. A literature search of available transport wing transonic flutter data is included.
Document ID
19830048630
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Myers, M. R. (Lockheed-Georgia Co. Marietta, GA, United States)
Guruswamy, P. (Informatics General Corp. Palo Alto, CA, United States)
Goorjian, P. M. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1983
Subject Category
Structural Mechanics
Report/Patent Number
AIAA PAPER 83-0922
Report Number: AIAA PAPER 83-0922
Meeting Information
Meeting: Structures, Structural Dynamics and Materials Conference
Location: Lake Tahoe, NV
Start Date: May 2, 1983
End Date: May 4, 1983
Accession Number
83A29848
Distribution Limits
Public
Copyright
Other

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