In order to study the swirl flow characteristics in the solid fuel ramjet combustor

a new type of inclined multihole swirler was designed

and the analytical formula of swirl number was deduced.The cold swirl flow field in the combustor was numerically simulated with different angles of the holes and different back pressures

while the swirl flow field structure and the total pressure recovery coefficient were studied.The relative error of the swirl number at the swirler outlet of the analytical formula was small as compared to the numerical results

thus meeting the engineering need.The swirl number at the dump combustor inlet can be changed by different angles of the holes and different back pressures.The central torroidial recirculation zone and the recirculation zone after the step of the dump combustor account for biggest total pressure loss.