An improved semiempirical method has been developed to estimate the static aerodynamics of configurations that use a trailing-edge flap for control. The method is based on deflecting the full aft-located lifting surface by an amount that allows the normal force coefficient to be equal to that generated by the deflected flap. A transfer in pitching moments and a modified axial force coefficient is derived to complete the set of static aerodynamics. The method is derived using theoretical methods that are a part of the 1998 version of the U.S. Naval Surface Warfare Center aeroprediction code and two sets of experimental data. Comparison of the improved method to available data shows that the method gives satisfactory results over the practical range for which trailing-edge flaps are contemplated for use. This practical range is an angle of attack less than 10 deg, Mach number of 2.0 or less, and flap deflections of less than 30 deg. However, additional wind-tunnel data are needed to refine and expand the applicability of the method. The additional wind-tunnel data requirement is particularly true for transonic Mach numbers and for supersonic Mach numbers where the angle of attack and control deflection are of the same sign.