Abstract
An experimental investigation of some effects of taper ratio on the flutter characteristics of as eries of thin cantilever wings having a sweptback angle of 45° and an aspect ratio of 4.0 has been conducted in the N. A. L. transonic blowdown wind tunnel for flutter testing at Mach numbers between 0.872 to 1.206. The results are presented as the ratios between the experimental flutter speeds and the reference flutter speeds calculated on the basis of incompressible two dimensional flow. These ratios, designated the flut ter speed ratios, are given as functions of Mach numbers for the wings tested. The flutter speed ratios were characterized by the minimum values at around Mach number 1.0 with the increase in the speed ratios in the range of subsonic and supersonic speeds investigated.
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