| A concept has been proposed for the adaptation of a pulse detonation rocket (PDR) into a type of scramjet in which the PDR ejects into a subsonic or supersonic secondary flow as a means of providing thrust. A model of such a configuration was developed and tested in the supersonic blow-down tunnel at the Aerodynamics Research Center (ARC) at the University of Texas at Arlington (UTA). This was done as a means of determining if this is a viable option for future propulsion.; All Mach 0 tests indicate that unsteady ejector performance is better than steady performance as was expected. Quantifiable results for thrust augmentation were obtained, but proved to be too optimistic when compared to data from other similar studies. A more accurate prediction of thrust augmentation could not be used due to the lack of knowledge of total pressure in the mixing interface, but it was determined that the secondary flow is relatively insensitive to the primary flow fluctuations, and higher frequency ejector rates drive the system to results closer to steady-state. As for supersonic test results, there was little to no effect on the secondary flow from the primary flow due to the large mass flow ratio between the secondary flow and the primary flow. |
