Wing Design for Subsonic Aircraft

Abstract

Major structural part of an aircraft is the wing which is used to produce the lift during flying conditions. Wing is inclined at certain angle of attack with stall regions. When the flow passes over an airfoil due to the pressure difference at top and bottom surface of the wing the lift force is generated. The aim of the present study is to design the rectangular wing of subsonic aircraft using 3D EXPERIENCE &analysis through SIMULIA with Al alloy to find von-mises stress which is developed in the wing design.The wing is designed in solid modelling software using 3D EXPERIENCE and analysis is done using finite element method by using SIMULIA. Static structural analysis of the wing is done to find deformation, stress, and strain induced in the wing structure wing. Production of the lift to drag ratio for the tailless aircraft is high. The stability of an aircraft is considered for the flying wing is dependent on the design and configuration of the wing construction for production of lift in major conditions of flight. With the known values of von mises stress and displacements and strainsthe region of slip where the failure may occur and zones of failures are introduced before braking through rectanngular wing structural analysis.