A unified theory for the aerodynamics and noise of advanced turboprops are presented. Aerodynamic topics include calculation of performance, blade load distribution, and non-uniform wake flow fields. Blade loading can be steady or unsteady due to fixed distortion, counter-rotating wakes, or blade vibration. The aerodynamic theory is based on the pressure potential method and is therefore basically linear. However, nonlinear effects associated with finite axial induction and blade vortex flow are included via approximate methods. Acoustic topics include radiation of noise caused by blade thickness, steady loading (including vortex lift), and unsteady loading. Shielding of the fuselage by its boundary layer and the wing are treated in separate analyses that are compatible but not integrated with the aeroacoustic theory for rotating blades. Hanson, D. B. Unspecified Center AEROACOUSTICS; AIRCRAFT NOISE; COUNTER ROTATION; FLOW DISTRIBUTION; HIGH SPEED; TURBOPROP AIRCRAFT; VIBRATION; VORTICES; APPROXIMATION; BOUNDARY LAYERS; DISTORTION; FUSELAGES; LOADS (FORCES); NONLINEARITY; NONUNIFORMITY; SHIELDING; THICKNESS; WAKES; WINGS...