Abstract: A missile with tilt-wings in "X-X" configuration is considered in supersonic flight at small angle of attack and sideslip angle.When the pitch and yaw of the missile are controlled by means of deflection of its wings,the non-symmetrical load distrbution on the wings appears and induce a rolling moment.The aerodynamic loads on the wings caused by aerodynamic interference in deflection of the wings at certain angles have been studied on the basis of the slender-body theory concerning the problems of thickness,angle of attack and sideslip angle.The equation for calculation of the induced rolling moment on the wings has been formulated.It is found that the value of the induced rolling moment on the wings depends on the flight condition,the aerodynamic configuration and the control of the missile,but it is small as usual.