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Aircraft Wing Essay

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Design and Analysis of aircraft Wing

Suraj Kumar

K L University, Green Fields, Vaddeswaram, Guntur District, A.P, INDIA, 522502 Department of Mechanical Engineering, (id no.-13007522)

Abstract:
This deals with bending Finite Element Analysis of the aircraft wing using commercial software ANSYS. An aircraft wing is made of composite with fibre angles in each ply aligned in different direction. Various air foil thickness and ply angles were considered to study the effect of bending-torsion decoupling. The laminate characteristics are usually calculated using the number of layer, stacking sequence, geometric and mechanical properties. A finite number of layers can be combined to form so many laminates. The only restriction that is imposed on the laminate as an element of composite structure concerns its total thickness which is assumed to be much smaller than the other dimensions of the structure.
Aircraft wing model as per the plan should be made in FEA and the model is subjected to various loading. The loading given by the self-weight or due to acceleration due to gravity was discussed and the deflection over here should be calculated. The wing model is severely affected by the loads on along wing direction, across wing direction, vertical direction.NACA 2412 airfoil was taken for designing wing. FLUENT was used for computational fluid dynamic analysis to determine the lift and drag for wing during zero degreed flaps and angled

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