Strutjet engine performance

To increase the technology readiness level of hypersonic scramjet technology, an innovative strut-based dual-mode ramjet engine design capable of powering a hypersonic vehicle at speeds from Mach 4 to 8 is investigated. Two versions of the engine are under development: a dual-mode (ramjet/scramjet) engine for missile applications and a rocket-based combined cycle engine for space access. This paper will discuss the features of the dual-mode engine design and how they contribute to overall engine performance. Engine component performance was evaluated using a combination of analysis and component testing. Inlet performance data (mass capture, pressure recovery, and inlet/isolator pressure ratio) were obtained from wind-tunnel testing and correlated with model and full-scale computational fluid dynamics (CFD) analyses. Combustor performance data (combustion efficiency, fuel-injection performance, and pressure distributions) were obtained from full-scale direct-connect combustor testing. Nozzle losses and efficiency were obtained from CFD analysis. Performance parameters derived from these component tests and analyses were fed into a standard hypersonic engine cycle code to predict flight engine performance. The demonstrated component performance values were extrapolated to determine predicted component performance at the end of engine development, which were used to compute the vision flight engine performance.