Investigation on strut-based RBCC engine configuration to improve performance in M3-6

For the full flow path of unilateral expanded configuration of the RBCC engine, through three-dimensional numerical simulation and ground connect-direct tests analysis the influence of the structural parameters of the combustion chamber and flame stabilization to the performance of ramjet mode and scramjet mode. Results show that in the case of Mach 4 and 6, three oblique shocks intersect in the inlet lip and inlet work stable. At Mach 3, the insufficiency of anti-pressure ability lead prequelling of normal shock and cause actual capture flow decreasing, inefficient combustion. Meanwhile, increasing the transverse spacing distance can expand the lateral combustion area and enlarge the range of the high pressure zone of the combustion chamber; When rockets are off, stable high pressure zone of the combustion chamber is built between the pylon and rear cavity and keeps efficiency of combustion is high.