In order to research the change regulation of aerodynamic center based on a variable forwardswept wing (VFSW) configuration with a slide way sweeping , by adopting a format of NS control equations with the method of finite volume method, the aerodynamic center on the VFSW configuration under different conditions is numerically simulated, and the location of the aerodynamic center is obtained. The change regulation of aerodynamic center with the sweep angle in the same Mach number and the change regulation of aerodynamic center with Mach number at the same sweep angle are summarized. The corresponding reason is analyzed through surface pressure contour over configuration and pressure coefficient on the wing. The results show that the aerodynamic center moves backward slightly and then reverses heavily with the increase of sweep angle in the same Mach number. With the increase of flight Mach number, the aerodynamic center moves forward in a tolerance interval at the same sweep angle. When the VFSW configuration executes corresponding missions, this makes an aerodynamic center moveable in a small scale.