Abstract
Described were the overview of the performance-estimation models for a propulsive pulse detonation engine (PDE), and the performance of the actual flight model of a pulse detonation rocket engine (PDRE-FM). As the performance-estimation models, the wave-dynamics model and the thermodynamics model were touched on. Furthermore, the homogeneous-dilution model of a partially-fueled detonation tube was introduced. The performance of the actual PDRE-FM was analyzed by using the homogeneous-dilution model and the thermodynamics model. It was found that the measured specific impulse of the actual PDRE-FM was reasonable.
