Abstract : This document describes the three-year effort to develop computational methodologies for the modeling of a hydrogen-peroxide based monopropellant micro-thruster operation. Computational models have been developed in two primary areas: (1) the numerical simulation of supersonic viscous flow in linear micronozzles; and (2) numerical simulation of chemical decomposition in micro-scale catalytic beds. in the case of the former, results are provided which describe the determination of `optimal' nozzle angles which maximize thrust production as a function of the flow conditions. This optimal angle was found to be approximately 25-30 degrees. Additional results delineate the importance of heat transfer and 3-D geometric effects. In the case of the latter, a combination of approximate, semi-analytical and fully computational models for simulating catalyzed monopropellant decomposition in micro-channels have been used to obtain predictions of minimum catalyst bed length required for complete decomposition; predictions suggest catalyst bed lengths of approximately 1-2 mm are necessary which are compatible with MEMS-type configurations.