The aim of this experimental work was a study of the influence of injection angle on the penetration and breakup of liquid jets in a supersonic airstream. All tests were conducted in the VPI 23-cm Supersonic Wind Tunnel at M=3,0 with T 0=ambient and P 0=4.35 atm. A particular goal was to incorporate injection angle into the penetration correlations previously developed at VPI. This was accomplished. A secondary aim of the work was to assess the performance of liquid fuel jet injection from the top of a strut. This is one method that has been suggested for the 'mechanical' enhancement of penetration. The penetration behavior was found to be essentially the same as for injection from a flat plate. A result of interest was the discovery of waves with sharp crests on the windward side of the jets for downstream angled injection. (Stoehr)


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    Titel :

    Effect of injection angle on liquid injection in supersonic flow


    Weitere Titelangaben:

    Einfluss des Einspritzwinkels bei der Fluessigkeitseinspritzung in Ueberschallstroemungen


    Beteiligte:
    Baranovsky, S.I. (Autor:in) / Schetz, J.A. (Autor:in)

    Erschienen in:

    AIAA Journal ; 18 , 6 ; 625-629


    Erscheinungsdatum :

    1980


    Format / Umfang :

    5 Seiten, 12 Bilder, 6 Quellen



    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch




    Effect of Injection Angle on Liquid Injection in Supersonic Flow

    S. I. Baranovsky / J. A. Schetz | AIAA | 1980


    Low angle injection into a supersonic flow

    MAYS, R. / THOMAS, R. / SCHETZ, J. | AIAA | 1989



    Liquid jet injection into a supersonic flow

    KUSH, JR., E. / SCHETZ, J. | AIAA | 1972


    Liquid Jet Injection into a Supersonic Flow

    EDWARD A. KUSH AND JOSEPH A. SCHETZ | AIAA | 1973