The present paper examines the benefits of increasing the compression ratio within the ejector section of a simple ejector/rocket. Relying on the ejector effect alone, the obtainable thrust is compared to that of both a hydrogen and kerosene fuelled first stage rocket engine typical of those used for space launch. At static sea level conditions, it is found that increasing the compression ratio is more beneficial than increasing the entrainment ratio in terms of thrust augmentation, while the benefit is reduced at higher flight altitude and speed. The hypothesis of using exit area constriction as a means of increasing ejector performance is also examined.

Additional Metadata
Keywords Compression, Ejector, Launch, Performance, RBCC
Conference 25th Congress of the International Council of the Aeronautical Sciences 2006
Citation
Etele, J, & Sislian, J.P. (2006). Analysis of increased compression factor on ejector-rocket performance. Presented at the 25th Congress of the International Council of the Aeronautical Sciences 2006.