In order to learn the influential factors of nozzle performance of hot water rocket motor deeper

numerical simulation of the flow field in the nozzle were performed at different parameter conditions. The impact rules of different initial conditions such as pressure

vapor volume fraction

supercooling and different nozzle structures such as expansion ratio

converging half-angle and expansion half-angle to the thrust were investigated. The calculating results show that: the greater the initial pressure

the greater the thrust; as the initial vapor volume fraction increases

thrust has a process of increase first and then decrease; thrust is larger when the initial temperature of hot water rocket motor is closer to the saturation temperature; thrust has a process of increase first and then decrease with the increasing of expansion ratio; the impact of converging half-angle to the thrust is minor; the greater the expansion half-angle

the smaller the thrust.