An experimental investigation was conducted to determine the thrust coefficient of a high-area-ratio rocket nozzle at combustion chamber pressures of 12.4 to 16.5 MPa (1800 to 2400 psia). A nozzle with a modified Rao contour and an expansion area ratio of 1025:1 was tested with hydrogen and oxygen at altitude conditions. The same nozzle, truncated to an area ratio of 440:1, was also tested. Values of thrust coefficient are presented along with characteristic exhaust velocity efficiencies, nozzle wall temperatures, and overall thruster specific impulse.


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    Titel :

    Experimental Performance of a High-Area-Ratio Rocket Nozzle at High Combustion Chamber Pressure


    Beteiligte:
    R. S. Jankovsky (Autor:in) / J. M. Kazaroff (Autor:in) / A. J. Pavli (Autor:in)

    Erscheinungsdatum :

    1996


    Format / Umfang :

    28 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Experimental performance of a high-area-ratio rocket nozzle at high combustion chamber pressure

    Jankovsky, Robert S. / Kazaroff, John M. / Pavli, Albert J. | NTRS | 1996


    Experimental Performance of a High-Area-Ratio Rocket Nozzle at High Combustion Chamber Pressure

    Jankovsky, R. S. / Kazaroff, J. M. / Pavli, A. J. et al. | British Library Conference Proceedings | 1995



    Experimental Thrust Performance of a High-Area-Ratio Rocket Nozzle

    A. J. Pavli / K. J. Kacynski / T. A. Smith | NTIS | 1987


    Experimental thrust performance of a high area-ratio rocket nozzle

    Pavli, A. J. / Kacynski, K. J. / Smith, T. A. | NTRS | 1986