Experimental study on Dynamic Characteristics of Combustion Mode Transition in a Strut-based Scramjet Combustor Model

摘要

The supersonic combustion ramjet (scramjet) engine is expected to the most efficient propulsion system in the hypersonic flight regime. Given the broad range of aero-thermodynamic conditions experienced during hypersonic flight, the scramjet would operate under different combustion modes, and mode transition is a critical phenomenon in designing such engines, because the thrust and specific impulse of the fuel in each mode varies considerably.