The paper examines the aeroacoustics associated with model nozzles operating supersonically. In particular, the shock structure and radiated shock noise of Mach 1.5 and 2.0 nozzles are compared with those of a convergent nozzle over a wide nozzle pressure ratio range corresponding to a fully expanded Mach number between unity and 2.37. The nozzles were operated unheated both with and without a tab for screech tone suppression. The measurements show differences between the shock cell spacing of convergent and convergent-divergent nozzles, and the scaling relation appears to be a function of the exit-to-throat velocity ratio of each nozzle type. The acoustic measurements indicate the extent of the pressure ratio range where a C-D nozzle achieves a noise reduction benefit. At the design point of the Mach 1.5 nozzle, the total integrated sound power from this nozzle is 6 dB less than a convergent nozzle operating at the same pressure ratio and thrust


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Experiments of shock associated noise of supersonic jets


    Beteiligte:
    Seiner, J. M. (Autor:in) / Norum, T. D. (Autor:in)

    Kongress:

    American Institute of Aeronautics and Astronautics, Fluid and Plasma Dynamics Conference ; 1979 ; Williamsburg, VA


    Erscheinungsdatum :

    01.07.1979


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



    Shock-associated noise in supersonic jets

    PAO, S. P. / SEINER, J. M. | AIAA | 1983


    Shock-associated noise in supersonic jets

    Pao, S. P. / Seiner, J. M. | NTRS | 1983


    Broadband Shock Noise from Supersonic Jets

    T. D. Norum / J. M. Seiner | AIAA | 1982