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

Juhasz, Albert J

关键词: NOZZLE THRUST COEFFICIENTS;    CONVERGENT-DIVERGENT NOZZLES;    PROPELLANT PROPERTIES;    SPECIFIC HEAT;    COMPUTER PROGRAMS;    MOLECULAR WEIGHT;    ROCKET THRUST;   

RP-ID  :  NASA/TM—2019-220164,E-19681,GRC-E-DAA-TN64584

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来源: NASA Technical Reports Server

【 摘 要 】

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".