In order to meet the needs of flight performance, a tandem drive variable camber wing is designed with NACA4412 airfoil. Wing structure is divided into five sections along chordwise, and leading section is the main load-bearing structure. Four wing sections of the trailing edge are driven by four electrical servo motors in series. In the interior of deflecting wing section, pentahedron truss structure is adopted, and in the interior there is laid on the surface a composite elastic skin. Connecting rods with stop function is arranged to limit the relative rotation angle of the four trailing sections. A kinematics analysis model of the variable camber wing is established, and the drive speed is calculated. An aerodynamic analysis model of the wing is built, and the aerodynamic performance of four typical flight status is analyzed, and their performance is compared with that of the wing with conventional flight control surfaces. The results show that under the same flight status, the actuation time of the variable camber wing with fourstage tandem drive along chordwise is only 25% of that of the conventional wing. The lift-drag ratio increases by 71.94% for takeoff. The maneuver moment increases by 12.46% for roll. The lift increases by 11.19% for approach, and the drag increases by 104.83% for deceleration after touchdown. Tandem drive variable camber wing is superior relatively to the conventional control wing in handling characteristics and in aerodynamic performance.