An experimental study was conducted on 15° slanted entry nozzle to compare with same geometry straight entry Convergent-Divergent (CD) nozzle. The nozzle with design Mach number of 2.94 placed in a Mach 1.8 flow reveals that the nozzle can choke and deliver supersonic flow at its exit. In this paper the wall static pressure distribution along the length of the straight and slanted entry nozzle and its comparison with isentropic flow is discussed. The tests were conducted at different Nozzle Pressure Ratios (NPR) of the driving nozzle ranging from 3 to 7. The variation of inlet and exit Mach numbers for both straight and slanted entry nozzles run by a supersonic stream is also discussed. The separation location obtained by present experiment and from other empirical relations is compared.


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    Titel :

    Flow Characteristics of Straight and Slanted Entry Nozzle Run by a Supersonic Stream


    Weitere Titelangaben:

    Sae Technical Papers


    Beteiligte:

    Kongress:

    General Aviation Technology Conference & Exhibition ; 2006



    Erscheinungsdatum :

    30.08.2006




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    Performance of Slanted Entry Nozzle Run by a Supersonic Stream

    Kumar, C. / Elangovan, S. / Lovaraju, P. et al. | British Library Conference Proceedings | 2006


    Performance of Slanted Entry Nozzle Run by a Supersonic Stream

    Kumar, C. / Elangovan, S. / Lovaraju, P. et al. | AIAA | 2006


    Flow Characteristics in a Convergent-Divergent Nozzle Kept in a Supersonic Stream

    Senthil Kumar, C / Elangovan, S / Stanley, A J et al. | AIAA | 2005


    Exploratory Passive Control Study of a Supersonic Multi-Stream Nozzle Flow

    Gist, Emma D. / Doshi, Parshwanath S. / Kelly, Seth W. et al. | AIAA | 2020


    Swirling supersonic nozzle flow

    DUTTON, J. C. | AIAA | 1987