先端後退翼の遷音速フラッタ特性に関する実験的研究

抄録

Some experimental investigations on the transonic flutter characteristics have been conducted by the use of thin plate cantilevered wing models with sweptback tapered tips, which were elastically supported at the root, in the NAL 0.6m×0.6m transonic blowdown wind tunnel for flutter testing in the range of Mach numbers from 0.804 to 1.171.
The wing models have the tip planform of sweptback angles of 35° at the leading edge and 30°at 1/4 chord line, and aspect ratio of 1.017 and taper ratio of 0.6.
It is concluded that the flutter boundaries of the wing models have been obtained and the boundaries expressed by the "experimental flutter speed coefficient" are characterised by having the minimum values at around Mach number of 1.0, and that the considerable increase of flutter instability area is caused by the decrease in the stiffness of elastic support at the root of the model.