Akademik Veri Yönetim Sistemi
International Journal of Hydrogen Energy, cilt.214, 2026 (SCI-Expanded, Scopus)
This study examines two- and three-dimensional (2D and 3D) numerical simulations of a Rotating Detonation Engine (RDE) with an aerospike nozzle at the end of the combustion chamber. Two different nozzle geometries and two distinct ambient pressures were analyzed extensively. Detailed flow-physics analyzes were conducted revealing the presence of recirculation zones due to the base geometry of both nozzles. A novel concept, “delay time”, was introduced. The interaction between turbulence and the RDE flow-field was illustrated using Q-criterion iso-surfaces. The structure of detonation wave was investigated by Numerical Schlieren (NS) contour plots. To facilitate a comprehensive comparison of the nozzles' performance, several performance metrics were determined, including thrust, specific impulse, propulsive efficiency and coefficient of thrust. The thrust and specific impulse levels of the NPR-10 (Nozzle pressure ratio) and the NPR-25 nozzles were analyzed, revealing that the NPR-25 nozzle outperforms the NPR-10 nozzle in all ambient pressure levels.