Numerical study of air-breathing two-phase rotating detonation engine under Ma 6 flight conditions

Abstract

Air-breathing two-phase rotating detonation engines possess high thermodynamic cycle efficiency and have attracted extensive attention in domain of wide range flight aircraft. In this study, an engine configuration is proposed, and the corresponding numerical model is established using the Euler-Lagrange method. The engine type is suitable for flying at an altitude of 28 kilometers and a flying speed of Ma 6. Our data show that the engine operates primarily in chaos in this flight state. The peak pressure of the detonation wave is about 0.85 MPa, the peak temperature of the detonation wave is about 4500 K, the average thrust of the engine is 2637 N, and the average fuel-specific impulse is about 2989 s.