Engine/aircraft integration is a major factor for performance characteristics of hypersonic propulsion. A two-dimensional analysis of an airbreathing combined turbofan-ramjet propulsion system is presented with special emphasis on integration aspects of mixed compression air inlets and single expansion ramp nozzles. Based on performance analysis a real-time engine simulation program, integrated into a flight simulator, is presented. In a realistic flight-mechanical analysis of hypersonic aircraft, steady state and dynamic propulsion system performance have to be considered, with thrust and lift components and resulting pitching moments. Active thrust vector control has to be performed using variable inlet and nozzle geometry. At high flight Mach numbers the net thrust vector is very sensitive to inlet ramp deflection angles and angle of attack. The net thrust vector can easily be turned to more than 90°. Various propulsion system failure scenarios are presented.

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