CFD AND STRUCTURAL ANALYSIS OF AIR CRAFT WING USING RIBS AND SPARS

Abstract

Wing structure consists of skin, ribs and spar sections. The spar carries flight loads and the weight of the wings while on the ground. Other structural and forming members such as ribs are attached to the spars, with stressed skin. The wings are the most important lift- producing part of the aircraft. The design of wings may vary according to the type of aircraft and its purpose. In this thesis, project detailed design of trainer aircraft wing structure made by using CATIA. Then stress analysis of the wing structure is carried out to compute the stresses at wing structure. The stresses are estimated by using the finite element approach with the help of ANSYS to find out the safety factor of the structure. In a structure like airframe, a fatigue crack may appear at the location of high tensile stress. Life prediction requires a model for fatigue damage accumulation, constant amplitude S-N (stress life) data for various stress ratios and local stress history at the stress concentration. The response of the wing structure will be evaluated. In this thesis, the trainer aircraft wing structure with skin, spars and ribs is considered for the detailed analysis. The wing structure consists of 15 ribs and two spars with skin. Front spar having „I‟ section and rear spar having „C‟ section. Stress and fatigue analysis of the whole wing section is carried out to compute the stresses and life at spars and ribs due to the applied pressure load. CFD analysis is determine the pressure drop, velocity and mass flow rate by increasing the blade angles of the air craft wing at different speed. Modelling done in CATIA software analysis done in ANSYS software