This paper analyses deflection of an aircraft wing under various loading (uniformly distributed loading and point concentrated loading) conditions at the edges and the nodes and boundary conditions (fixed support, roller support and free) using JAVA code. The JAVA code was used to develop a computer interactive model. Classical plate theory and plane stress assumptions were made. Finite element analysis was used to carry out analysis on the wing which was taken as a thin plate. The wing was discretized with triangular and rectangular meshing. The aircraft wing considered is Airbus A320 wing. The interactive model developed analyzed different cases with different boundary conditions and loading conditions. Two cases were analyzed and deflection (lateral displacement) along X – axis, Y – Axis and XY – Axis for each case were presented. It was discovered that the greater the load, the higher the deflection obtained and for edges and nodes with fixed and roller support, higher loadings has to be applied for deflection to occur.
Keywords : Aircraft Wing, Plate theory, Finite Element Analysis, Loadings, Deflection.