Supersonic aircraft require propulsion systems that are significantly different from those for present subsonic aircraft. The higher jet velocity of the supersonic aircraft engines will generate more noise during the actual takeoff run than conventional jet transport engines. An applied research program was conducted at The Boeing Company from February 1966 through March 1971 to investigate jet nozzle systems which will suppress jet noise levels from the supersonic transport with minimal thrust loss. These efforts applied to the two prototype supersonic transports being developed at that time as well as the commercial version of the SST that was to follow. The research program indicated that 12 to 20 PNdB noise suppression can be attained with less than 10 thrust loss by using multielement jet nozzle concepts. This report summarizes the test results pertaining to suppressor nozzle noise and thrust characteristics.