Abstract
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.
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