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:

    Erscheinungsdatum :

    1996-06-01


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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