Static Structural & Modal Analysis of Aircraft Wing with Different Proportions with Aluminium

In this thesis, The project details the study of the general aviation of the airplane wing is Design & Analysis. Which design process starts with asketch how the aircraft plane is can be visualized. & the estimation based by the weights on the material properties & sketechs are been concluded by with it these can acquires the external geometries of the airplane. The which in these knows the different types of the materials are been used with design of an aircraft wing which analysis as been made by with it, the some of the metallic materials & non-metallic materials properties of the materials were be studied under the aircraft wings. The 3-d layout of the aircraft wing is been studied. In order to solve the problems we are designed a stiffened panel section & by the changing of the materials, the aircraft skin can withstand the a deformations of an structural weights has been always been important in the aircraft manufacturing industry, by using CATIA & Meshing in Hyper mesh & analysis is be done by ANSYS. Of the software are been considered with stiffened panel by it. Aluminium is the common element which is used in the design of an aircraft, but carbon fiber is recently being used in the airctaft.