The original purpose of FGMs was the development of super resistant materials for propulsion systems. In the present work, numerical and experimental techniques are used to investigate the dynamic behavior of generally laminated composited beams. In the numerical analysis, the laminated beam is modeled using the commercial finite element software ANSYS. In the experimental study the core and face materials of sandwich beam specimens are nylon/epoxy FGMs and pure epoxy laminates respectively. The dynamic behavior of the sandwich composite beam specimens with different fiber orientation was carried out using two dynamic excitation techniques, harmonic using harmonic response and impulse using hammer. The specimens were prepared in the following configurations, different orientation angles, different layers, and different thickness. The results reveal that the natural frequencies of sandwich beam were affected directly by the face materials. The natural frequency decreases with increasing fiber orientations of the nylon/epoxy face laminates. Increasing the thickness increases natural frequencies. This study concluded that it is useful for the designers to select the fiber orientation angle to shift the natural frequencies as desired or to control the vibration level.