This report describes development of a variable area ratio C-D nozzle numerical computational code "THRST", applicable to the evaluation of nuclear or chemical rocket performance. The propellant for the nuclear rockets is para-hydrogen with gas properties supplied by a sub-routine, while properties for chemical thrusters need to be user input. Detailed documentation of input and output variables and sample output listings enable the report to function as a "User Manual".


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    Titel :

    Converging-Diverging Nozzle Thruster Code for Nuclear or Chemical Rocket Performance Computations


    Beteiligte:

    Erscheinungsdatum :

    01.04.2019


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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