Numerical Study and Performance Evaluation for Pulse Detonation Engine with Exhaust Nozzle

The propulsive performance was estimated for the H2/Air PDE with a convergingdiverging exhaust nozzle using multi-cycle two-dimensional limit cycle simulations with the detailed chemical reaction model. The present simulation also compared with a variable property model reported in the literature. The overall features such as the effects of filling fraction, nozzle configuration, and flight condition in the present results are in agreement. The present results show that optimum rth/rtube for Ispf are 0.6 and 0.5 for M=2.1 and 3.5, respectively.