Numerical analysis of inflow equivalence ratio on jet-induced oblique detonation waves

As a hot topic in the research of hypersonic engines, oblique detonation engines have attracted the focus of researchers around the world in recent years. In an attempt to eliminate the possible reflux region structure commonly observed near the corner of the upper boundary of the oblique detonation combustion chamber in practical applications, as well as to effectively regulate both the initiation and surface positions of the oblique detonation wave (ODW), this research employs a scheme characterized by setting jet nozzles on the wedge surface. In the meantime, by solving the two-dimensional Navier-Stokes equations containing the source terms of chemical reaction, this research further investigates the foregoing phenomena. Relevant research findings reveal that introducing a jet with sufficient total pressure onto the wedge surface is beneficial to realize the early ODW initiation and furnish effective control over its initiation position. While significantly reducing the area of the reflux region, the proposed method is capable of avoiding the formation of a Mach reflection structure by varying the position and total pressure of the jet. Furthermore, with the help of this method, the existence of viscosity will advance the jet-controlled ODW's initiation position. Moreover, the proposed method characterized by the jet-controlled ODW is suitable for diverse incoming flow equivalence ratios (ERs).