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An Interactive Software for Conceptual Wing Flutter Analysis and Parametric StudyAn 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 for Macintosh or IBM compatible personal computers, on MathCad application software with integrated documentation, graphics, data base and symbolic mathematics. The analysis method was based on non-dimensional parametric plots of two primary flutter parameters, namely Regier number and Flutter number, with normalization factors based on torsional stiffness, sweep, mass ratio, taper ratio, aspect ratio, center of gravity location and pitch inertia radius of gyration. The parametric plots were compiled in a Vought Corporation report from a vast data base 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 Corp. 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
19970005613
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Mukhopadhyay, Vivek
(National Aeronautics and Space Administration. Langley Research Center Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
August 1, 1996
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NAS 1.15:110276
NASA-TM-110276
Accession Number
97N13414
Funding Number(s)
PROJECT: RTOP 505-69-59-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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