In this research, the numerical method and the wind tunnel test were adopted to investigate the characteristics of the rolling moments of the missile with curved wing. According to different arrangement of the wing which provides the basis information for rotating speed design, the rolling characteristics obtained by using both methods have the same trend, which validates the reliability of the numerical method. Two kinds of wing arrangement are promoted based on the obtained characteristics and can avoid rolling effect induced by the wings themselves, which is propitious to rotating speed design.