Low-Order Parametric Analysis of a Rotating Detonation Engine in Rocket Mode

Abstract

A low-order analytical performance model for the rocket-mode rotating detonation engine was developed. Starting from the general form of the continuity, momentum, and energy equations and integrating over an annular control volume, expressions for the resultant force in the axial and circumferential directions were formulated and used to calculate a range of performance metrics including thrust, specific impulse, relative force ratio, and mean exit swirl angle. This model was then used to conduct a parametric analysis of the rotating detonation engine to determine the effect of varying several engine design parameters on performance. Increased propellant pressure, lower propellant temperature, and zero injection swirl were found to increase performance. Wider and shorter annuli offered increased thrust and specific impulse. Exit swirl was seen to be nonzero for the majority of design iterations, resulting a resultant torque on the control volume. However, some zero-torque points were observed, which may prove especially valuable in design optimization endeavors. The present results agree qualitatively with reported numerical simulations.