@techreport{oai:jaxa.repo.nii.ac.jp:00044898,
 author = {中井, 暎一 and 森田, 甫之 and 菊池, 孝男 and NAKAI, Eiichi and MORITA, Toshiyuki and KIKUCHI, Takao},
 month = {Feb},
 note = {An experimental investigation has been conducted on the transonic flutter characteristics of low aspect ratio thin sweptback all-moving tail surface models, which were supported by a simulated fuselage beam. These experiments were conducted in the NAL 60cm×60cm transonic blowdown wind tunnel for flutter testing, at Mach numbers from 0.873 to 1.129. The tail surface has sweptback angles of 42.5deg at the leading edge and 10deg at the trailing edge, an aspect ratio of 1.394, and a taper ratio of 0.318. The wing models have been supported by the narrow width at the root. Some effects of an added mass at the leading edge of the wing tip on the flutter characteristics were also studied. Added mass improved the transonic flutter characteristics. It is concluded that the flutter boundaries for the tail surface models were obtained, and that the flutter boundaries expressed by the experimental flutter speed coefficients are characterized by having a minimum value at around Mach number 1.0 in the range of Mach numbers used., 資料番号: NALTR0643000, レポート番号: NAL TR-643},
 title = {An Experimental Investigation on Transonic Flutter Characteristics of Low Aspect-Ratio Sweptback All-Moving Horizontal Tail Surface Modesl},
 year = {1981}
}