International Journal of Aerospace Engineering / 2015 / Article / Fig 3

Research Article

Nonlinear Vibrations of FGM Cylindrical Panel with Simply Supported Edges in Air Flow

Figure 3

(a) and (b) depict the bifurcation diagrams of versus the first two modes and which are given when the volume fraction index is taken to be 0.5. The Mach number is taken to be 5.0. The magnitude and frequency of the in-plane excitation are taken to be and 161 Hz, respectively. (c) and (d) are partially enlarged details for (a) and (b), respectively. The value of horizontal coordinate is defined as .
(a)
(b)
(c)
(d)