A theoretical analysis is presented for calculating the normal force and center of pressure on plane wing/body combinations exhibiting leading edge separation. The mathematical model for the separated flow involves the shedding of a number of discrete vortex pairs along the wing leading edge, each pair satisfying the Kutta condition at the position of shedding. The subsequent lateral positions of these vortex filaments are calculated step by step, so that the rolling up of the vortex sheet is taken into account. Hence, the method predicts the chordwise normal-force distributions as well as the vortex sheet shapes over the configuration.