薄い片持後退角翼の遷音速フラッタ特性におよぶす一つの集中質量の位置の影響について

その1 スパン方向位置シリーズ

抄録

An experimental investigation of some effects of spanwise location of one, engine-pod like, concentrated mass on transonic flutter characteristics of thin cantilever wings having a sweptback angle of quarter chord line of 20° and panel aspect ratio and taper ratio of 4.0 and 0.4, respectively, has been conducted in the N.A.L. 60cm×60cm transonic blowdown wind tunnel for fiutter testing at Mach numbers between 0.759 and 0.963.
The experimental results are presented in comparing the boundary of fiutter density and egperimental flutter-velocity coefficient of the respective wing-pod configuration experimented, as a function of Mach number, and also are compared with the calculated results by the matrix iteration method employing two-dimensional incompressible unsteady flow theory as required oscillatory aerodynamic forces.