Ignition mechanisms of pulse detonator initiated scramjet cavity

A fueled cavity in a supersonic crossflow was ignited via pulse detonator (PD) producing detonation waves that were then decoupled to produce varying degrees of shock-flame separation at the exit PD tube. This decoupling allowed for observation ignition mechanism, and key parameters required successful identified. Measurements made using high-frame-rate OH Planar Laser-Induced Fluorescence (PLIF) schlieren chemiluminescence imaging. It shown entrainment high-temperature intermediate species into forward region cavity, immediately behind step, is principal criterion ignition. Both coupled slightly cases induced significant shedding step region, leading flame stabilization within cavity. At conditions where did not occur, observed. In cases, there more due greater disturbances created flowfield. As degree increases, less therefore lower likelihood Additionally, time combustion reach its steady-state condition varied with detonation. Coupled be disruptive thus steady state than cases.