Numerical simulation of installed performance for parallel turbo-ramjet combined cycle engine

To investigate the installed performance of turbine based combined cycle engines, based on Hypersonic Strike Fighter proposed by Georgia Institute of Technology, parallel configuration was selected as a turbofan-ram combined engine. The work process and the determination of transition mode point of turbo-ramjet were described. The installed loss computational model and installed performance computational model were established. The installed performance characteristics of turbo-ramjet were simulated by numerical method. The investigation indicates that the engine installed performance can meet the requirement of aircraft.