Heat transfer studies of jet flow in a canister launcher

According to experiments and two-phase flow theories, a supersonic two-phase jet flow heat transfer coefficient model of a missile rocket is established to predict the heat transfer process in the annular space where between inner cylinder and outer cylinder of a CCL. Comparing the simulation results with the measurement values it shows that the established jet flow heat transfer coefficient model is able to describe the real heat transfer process in canister approximately. Calculation results also demonstrate that, the coagulate-state AI(2)O(3) particles mixing in jet flow are the main heat transfer factor which causes the cylinder wall's temperature rise high rapidly at initial stage of jet flow; the high temperature radiation and pure gas-phase convection heat transfer are the main heat transfer forms in the middle and terminal stage; heat transfer coefficients are in non-linear variations along cylinder wall. By revising some parameters, the heat transfer coefficient model can be applied to other types of missile canister launcher practically..