Cure behavior of carbon fiber reinforced phenolic composite was investigated to obtain the manufacture design data of high temperature and long lifetime ablative nozzle composites in rocket propulsion system. First of all, cure reaction of resin was studied to obtain the cure initiation temperature and the heat of cure by using the thermal analysis system. Flow behavior of resin and prepreg was studied by using the rheometric and dielectric analysis systems in order to obtain resin flow in composite, viscosity increase resulted from the cure reaction, and solidification behavior during cure. After the preliminary study, cure cycle of composite was obtained and composite had uniform temperature distribution during cure of composite. In this study, the pressurization point effect on cure cycle was investigated to get carbon fiber reinforced phenolic composite having no voids and blisters. By using the dielectric analysis systems pressurization points were selected by the ion and dipole mobilities of resin that have the information of resin flow and viscosity during cure of composite. Resin flow out ratio, 1 ply thickness, relative compaction ratio, density, residual volatile contents, and interlaminar shear strength of composites were tested with different pressurization points and it was found that the pressurization point during cure had great effect on compaction in carbon fiber reinforced phenolic composite.