Optimization of the thrust performance of a pulsed detonation engine

The problem of modeling the operation cycle of a pulse detonation engine and estimating its highest possible thrust performance is considered. Self-similar and non-self-similar flows in an axisymmetric duct of finite length and variable cross section which arise from detonation propagation from the closed end of the duct are studied for the model of an infinitely thin detonation wave. Analytical and numerical methods are used. Dependences of the average impulse and the average specific impulse on the shape of the side wall of the duct are investigated. The optimal shapes corresponding to the highest thrust performance of the operation cycle are found.