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Interactive flutter analysis and parametric study for conceptual wing designAn interactive computer program was developed for wing flutter analysis in the conceptual design stage. The objective was to estimate the flutter instability boundary of a flexible cantilever wing, when well defined structural and aerodynamic data are not available, and then study the effect of change in Mach number, dynamic pressure, torsional frequency, sweep, mass ratio, aspect ratio, taper ratio, center of gravity, and pitch inertia, to guide the development of the concept. The software was developed on MathCad (trademark) platform for Macintosh, with integrated documentation, graphics, database and symbolic mathematics. The analysis method was based on nondimensional parametric plots of two primary flutter parameters, namely Regier number and Flutter number, with normalization factors based on torsional stiffness, sweep, mass ratio, aspect ratio, center of gravity location and pitch inertia radius of gyration. The plots were compiled in a Vaught Corporation report from a vast database of past experiments and wind tunnel tests. The computer program was utilized for flutter analysis of the outer wing of a Blended Wing Body concept, proposed by McDonnell Douglas Corporation. Using a set of assumed data, preliminary flutter boundary and flutter dynamic pressure variation with altitude, Mach number and torsional stiffness were determined.
Document ID
19960018385
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Mukhopadhyay, Vivek
(NASA Langley Research Center Hampton, VA United States)
Date Acquired
August 17, 2013
Publication Date
September 21, 1995
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA Paper 95-3943
NAS 1.15:111260
NASA-TM-111260
Meeting Information
Meeting: 1st AIAA Aircraft Engineering, Technology and Operations Congress
Location: Los Angeles, CA
Country: United States
Start Date: September 19, 1995
End Date: September 21, 1995
Accession Number
96N23711
Distribution Limits
Public
Copyright
Public Use Permitted.
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