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

Abstract

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".