Numerical Simulations on the Thrust Performance of Nozzles and Detonation Propulsion of a Sudden Area Change Tube

Based on the homogenous fluid reaction N-S equations, the k- turbulent model and the EBU combustion model, the propagation of detonation wave in a sudden area change tube and the influences on the thrust performance of the main tube with different nozzles were investigated. Our results show that, a new detonation can be initiated promptly when the detonation wave of the pre-detonator injects into the main tube. In addition, with the mount of nozzle, the average thrust of single detonation varies. The head-end thrust increases with the raise of the contracting angle of nozzle, and decreases with the raise of its diverging angle. But the average total thrust increases with the diverging angle, and decreases with the raise of converging angle. There also exists an optimal diverging angle which can generate maximum average total thrust.