The gasdynamic structure of high altitude rocket plumes is investigated. A simple analytical model for the expansion of a gas into a vacuum is constructed and is shown to represent the expansion of exhaust gases from rocket motors into the region bounded by the inner shock wave and Mach disc. A comparison of the exhaust expansion model with solutions obtained with the method of characteristics is made and shows good agreement. Contours of constant density, electron density, and collision frequency in the exhaust plume of a typical rocket engine are determined. The blast wave theory of Hill et al is extended to allow the calculation of the size and shape of rocket plumes of solid propellant missiles. A method is derived which determines the plume drag of solid propellant motors. The method accounts for the fact that solid propellant rocket plume flow is a two phase flow of gas and solids and that the solids present in the exhaust take part in determining the mass flow but not the pressure or the expansion of the exhaust gases upon exit from the rocket nozzle. The plume expansion and resulting plume size is shown to depend on the thrust and the engine exit plane conditions of the gas phase of the two phase flow.


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    Title :

    High Altitude Rocket Plumes


    Contributors:
    P. O. Jarvinen (author) / J. A. F. Hill (author) / J. S. Draper (author) / R. E. Good (author)

    Publication date :

    1966


    Size :

    65 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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