VIBRATION AND CFD ANALYSIS OF AIR CRAFT COMPOSITE WING IN SUBSONIC AIR FLOW

Abstract: A wing is a type of fin with a surface that produces aerodynamic force for flight or propulsion through the atmosphere, or through another gaseous or liquid fluid. As such, wings have an airfoil shape, a streamlined cross-sectional shape producing lift. A wing's aerodynamic quality is expressed as its lift-to-drag ratio. The lift a wing generates at a given speed and angle of attack can be one to two orders of magnitude greater than the total drag on the wing. A high lift-to-drag ratio requires a significantly smaller thrust to propel the wings through the air at sufficient lift. The requirements for the aircraft wing are High stiffness, High strength, High toughness and Low weight. In this thesis, an aircraft wing will be designed and modeled in 3D modeling software Pro/Engineer. The materials used for aircraft wings are mostly metallic alloys. In this thesis, the materials are replaced by composite materials Fiber Glass, Boron Fiber and Ceramic Fiber. Static analysis and buckling analysis on the wing will be done to determine the stresses produced by applying loads. Vibration analysis will be done on the aircraft wing to determine the frequencies. CFD analysis will be done on the wing to determine the lift and drag forces by changing angle of attacks. Analysis will be done in Ansys.

Keywords: Glass fiber, Epoxy resin, Flyash, Hand lay-up method, FFT analyzer.