An experimental investigation of some effects of varied location of added mass at wing tip on transonic flutter characteristics of thin cantilever wings has been conducted in a transonic blowdown wind tunnel for flutter testing at Mach number between 0.819 and 1.192. The wings have sweptback angle of 42.5 at leading edge and of 10 at trailing edge, panel aspect ratio of 1.344 and taper ratio of 0.336. The flutter boundary expressed by the experimental flutter-velocity coefficient is characterized by having maximum values at around Mach number 1.03. The stable region expands by moving the C.G. location forward of the added mass. (Author)
Some Effects of Center of Gravity Locations of Added Mass on Transonic Flutter Characteristics of Low Aspect Ratio and Sweptback Thin Canitlever Wing
1973
15 pages
Report
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Englisch