Oblique detonation wave triggered by a double wedge in hypersonic flow

Pressure-gain combustion has gained attention for airbreathing ramjet engine applications owing to its better thermodynamic efficiency and fuel consumption rate. In contrast with traditional detonation induced by a single wedge, the present study considers oblique shock interactions attached double wedges in hypersonic combustible flow. The temperature/pressure increases sharply across interaction zone that initiates an exothermic reaction, finally resulting Oblique Detonation Wave (ODW). Compared case single-wedge ODW, double-wedge geometry great potential control initiation of ODW. As tentative study, two-dimensional compressible Euler equations two-step induction-reaction kinetic model are used solve dynamics triggered wedge. effects wedge angles corner locations on structures investigated numerically. results show ODW complex comprising three Shock Waves (OSWs), induction zone, curved front, unburned/low-temperature gas belt close surface second Both increasing angle downstream location lead abrupt OSW–ODW transition type, whereas former corresponds shock–shock later greater effect chemical process. Analysis polar flow scale confirms structure mainly depends coupling shocks heat release confined zone.