Propagation of Detonation Waves in a Supersonic Combustible Flow

Abstract

In the present study, propagation of detonation in a supersonic combustible flow was experimentally studied as a first step to realize the behavior of standing detonation for hypersonic propulsion. Experiments were performed in the detonation tube combined with a shock tube providing the supersonic flow of a stoichiometric oxyhydrogen. The flow Mach number behind the incident shock wave was estimated to be 1.2. The experimental results show that depending on the flow velocity, the apparent propagation velocity of detonation in the supersonic flow is higher in the upstream and lower in the downstream direction than the Chapman-Jouguet (CJ) velocity. The smoked plate records demonstrate cellular patterns deformed in the flow direction, which is due to velocity change of the leading shock front constructing the cellular structure. The calculated aspect ratios of the cell agree well with the experimental ones under the assumption that the velocity of the transverse wave is not affected by the flowing mixture.