Propulsive performance of pulse detonation engine with fluidically augmented nozzle

Both generalized 1-D flow model and constant volume cycle model are employed to investigate the performance of pulse detonation engine with a fluidic nozzle. Thrust coefficient of a fluidic nozzle in steady flow and average thrust coefficient of a pulse detonation engine with a fluidic nozzle during a pulse detonation cycle have been calculated. In the steady flow, fluidic nozzle shows a better performance than its baseline nozzle when nozzle pressure ratio is lower than a critical value. During a pulse detonation cycle, for a certain initial uniform combustion pressure, the fluidic nozzle with a continual second injection can augment the average thrust coefficient when the expansion ratio is higher than a critical value. Interrupted injection can improve the max average thrust coefficient for this initial uniform combustion pressure by 2.4% when initial uniform combustion pressure is 5MPa.