Influence of dual-side inlet swirl-injection on performance of solid rocket ramjet

Given the same inlet flow under the different swirl-mode working condition, the turbulent reaction flow field in the side inlet afterburning chamber of solid rocket ramjet was numerically simulated by means of Reynolds stress equation model and eddy-dissipation combustion model. Some thermodynamic parameters of combustion products including equilibrium ingredients and combustion temperature were obtained. On the basis of the above parameters, combustion efficiency and ramjet thrust in the afterburning chamber were also calculated. The numerical simulation results show that air inlet swirl injection can efficiently improve combustion efficiency in the chamber of side inlet solid rocket ramjet, so the performance of the ramjet can be further improved. Combustion efficiency follows the rule of first increase, and then decrease with the swirl injection intensity. The ramjet thrust can increase by about 2.3% by using optimal swirl number.