Combustion mode transition in a scramjet engine

The transition processes of supersonic combustion in a dual-mode scramjet were investigated by means of directly-connected tests under the simulated conditions corresponding to the flying alti- tude of 25 km and the Mach number of 6.Pressure distribution on the wall of the combustor and one- dimensional simulation indicate that the combustion mode transition can be carried out by altering fuel injection position and equivalence ratio.Comparison of switch sequences of different fuel-injection po- sition shows that the combustion mode changes are determined by the fuel distribution in a combustor, but the combustor has a certain ability to resist fuel disturbance.