An analysis procedure has been developed to predict propeller rotational noise during nonuniform, as well as uniform, inflow conditions. Although many studies have been conducted since the development of Gutin's equations (NACA TM I195), none have been developed that adequately describe the near and far rotational-noise fields of a helicopter rotor during forward-flight and maneuver conditions, where the rotor blades experience azimuthal pressure variations. This report presents a newly developed analysis that is an extension of the methods of Garrick and Watkins (NACA Rept. 1198). It removes many of the limitations of previous theory as applied to helicopter-rotor rotational noise. The rotor system is represented by a surface of stationary dipole radiators that simulate the normal pressure distribution on the rotor disk. The analysis utilizes blade-section loading, either measured or predicted, which contains both steady and varying components at integral multiples of the main-rotor rotational speed as a function of radius and azimuth. The analysis has yielded good correlation with measured helicopter-noise levels for various forward-speed and transient conditions. [Study partially supported under U. S. Aviation Materiel Laboratories Contract.]