Abstract: A wing camber command system (28) is provided for calculating the optimum camber of a wing (52) during aircraft operation. The wing (52) has at least one movable leading edge surface (42, 44) and at least one movable trailing edge surface (46, 48, 50) for varying wing camber, while maintaining smooth upper surface contours. Flight conditions and aircraft parameters including aircraft speed (30), normal acceleration (32), weight (34), and the dynamic pressure of air (36) are sensed during the aircraft maneuver. An onboard computer (40) monitors the sensed conditions and parameters and calculates a coefficient of lift therefrom. The computer contains stored data indicating the desired positions for the leading and trailing edge surfaces necessary to achieve a wing camber that optimizes the wing lift/drag (L/D) ratio during aircraft operation. The computer uses this stored data to command optimum wing camber.