Comparison of flutter calculations using various aerodynamic coefficients with experimental results for some rectangular cantilever wings at Mach number 1.3

Herbert C. Nelson, Ruby A. Rainey
naca-tn-3301
Nov 1954


A general Rayleigh analysis is used as a basis for developing four methods of flutter analysis that are applied to twelve low-aspect-ratio wings. These wings were previously tested at a Mach number of 1.3 by progressively varying certain wing parameters until flutter occurred.

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