Free Vibration Analysis of Tapered Composite Aircraft Wing via the Finite Element Method

The responses of the structures used in engineering applications under effects static and dynamic forces are significant design phase. Determination response for a structure is initially performed by evaluation free vibration characteristics that mode shape frequencies. This paper presents modal analyses tapered aircraft wing consist NACA4415 different common materials aviation industry. Furthermore, effect winglets on natural frequencies examined. main as ribs shells drawn using CATIA imported to ANSYS Workbench. Analyses have been carried out considering three-dimensional cantilever beam fixing one end (root chord) while other (tip free. first ten modes with their respective shapes aircrafts obtained. results show decrease frequency noticeably shell material Carbon Epoxy UD has observed higher compared Kevlar Epoxy.