Advanced Supersonic Transport jet noise may be reduced to Federal Air Regulation limits if recommended refinements to a recently developed ejector shroud exhaust system are successfully carried out. A two-part program consisting of a design study and a subscale model wind tunnel test effort conducted to define an acoustically treated ejector shroud exhaust system for supersonic transport application is described. Coannular, 20-chute, and ejector shroud exhaust systems were evaluated. Program results were used in a mission analysis study to determine aircraft takeoff gross weight to perform a nominal design mission, under Federal Aviation Regulation (1969), Part 36, Stage 3 noise constraints. Mission trade study results confirmed that the ejector shroud was the best of the three exhaust systems studied with a significant takeoff gross weight advantage over the 20-chute suppressor nozzle which was the second best.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Aerodynamic Performance Investigation of Advanced Mechanical Suppressor and Ejector Nozzle Concepts for Jet Noise Reduction. Final Report, 1981-1984


    Contributors:

    Publication date :

    1985


    Size :

    218 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





    Aircraft performance sensitivities to ejector nozzle concepts

    ORDONEZ, GUSTAVO / GEORGES, MARTIN | AIAA | 1991


    An investigation of a mixer-ejector nozzle for jet noise reduction

    Zaman, Khairul Q. / Bridges, James E. / Castner, Raymond S. et al. | AIAA | 2019


    A mixer-ejector noise-suppressor model

    Tew, David / Teeple, Brian / Waitz, Ian | AIAA | 1997


    Nozzle/ejector noise source characteristics

    Oishi, Tsutomu / Nakamura, Yoshiya / Strange, Paul | AIAA | 2001