This paper presents the research extensively carried out based on the static analysis for finding the optimum design of wing structure. The two types of wings (Rectangular wings) for unmanned airplanes were chosen and designed at the basis of M = 0.21 and at M = 0.4 respectively. Further it also covers both the aerodynamic and structural designs. The aerodynamics study was achieved by using the vortex lattice method using XFLR-CFDsoftware and the structural analysis was achieved by using the CATIA V5 package consisting of isotropic and composite materials. A wing structure consists of spars, ribs, reinforcements and skin and they were optimized considering two aspects of weight minimization, and critical load maximization. The wing carries an elliptically distributed load along the span. The design variables are based on the positioning of spars and ribs of the structure. The out come of the research clearly indicates the significant results in terms of objective functions obtained through the optimization procedures. When composite material is used instead of isotropic material mass saving of 34 % is achieved. The optimum design for each wing was obtained according to the mass, stress and displacement. This could be seen in the presentation subsequent

Keyworks: Structural analysis, optimization procedures.