Abstract: The development of advanced composites has opened up a vast vistas in aeronautical and astronautical industry.Recently composite lifting surfaces have been broadly researched in abroad.Aeroelastic tailoring is defined as the technology to design a lifting surface which exhibits a desired aeroelastic response.This paper is to illustrate an application of the aeroelastic tailoring concept for swept wings.Specifically,the application involves the design of composite material wing.T.A.Weisshaar presented a simple theory to predict the divergence behavior of moderate to swept laminated composite wings with high aspect ratio,The equations developed from the strip theory and the classical Euler-Bernoulli beam theory to predict the effect of laminat construction upon wing divergence.Wing taper ratio is of importance for the determination of the divergence speed where such a speed actually exists.However,decreasing the taper ratio tends to decrease critical swept angle,although these decreases are very small.There are some figures to show the behavior of flutter and divergence speed as function of fiber orientation for three sectional centre of gravity positions.The effect of wing aspect ratio has also illustrated.From aeroelastic viewpoint,the primary effect of the elastic coupling between bending and torsion of composites,introduced by the laminated material through the parameter k,can successfully negatect the undesirable influnce of forward swept on aileron operation efficency and divergence.