A numerical analysis was performed to predict the thermo-fluid dynamic characteristics of hydrazine monopropellant
reaction in the thruster combustor and nozzle. A 1-D porous model was introduced to simulate
catalytic reaction by iridium in the combustor while 2-D axisymmetric analysis was applied to predict the
nozzle flow. The chemical species and temperature variations were predicted by changing the injection pressure
and mass flow rate and their results were validated by comparison with limited experimental data. The
thrust variation with injection pressure could be estimated using the current 1-D combustor modeling.