The design and analysis of a simple jet noise reduction concept is discussed. The concept is intended for use on the type of supersonic exhaust nozzles typically employed on tactical aircraft. The concept addresses both broadband shock associated noise (BBSAN), and turbulent mixing noise. BBSAN is addressed through a reduction in the effective exhaust area, which reduces the strength of the shock cell structure in the jet. Turbulent mixing noise is reduced by enhancement of mixing in the jet shear layer, which creates a shorter region of strongly turbulent ow, and breaks up the large scale turbulent structures. This paper describes an active control device that de ects a fraction of the adjustable seals in the divergent section of the engine exhaust nozzle. After takeoff, the de ected seals would be returned to their unde ected position. Very favorable jet noise reductions are demonstrated at multiple observer angles for nominal takeoff conditions.