A nine-month exploratory development program was conducted to analyze, design, fabricate, and test hardware to gather data on the operation of an expansion-deflection nozzle. The technical effort consisted of the analysis and design of a nominal 25,000-lb thrust, 1500 psia chamber pressure, expansion-deflection thrust chamber using LO2/LH2 propellants at a mixture ratio of 6:1. Several chamber segments and an annular uncooled thrust chamber were designed using an anticipated flight configuration thrust chamber design as a baseline. An annular and a segment injector were analyzed and designed for use on the thrust chambers. The segment injector and both water-cooled and heat sink chambers were fabricated and tested at sea level conditions. The injector demonstrated acceptable operation at chamber pressures of 300 and 750 psi.


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    Experimental and CFD Analysis of the Expansion Deflection Nozzle

    Taylor, N.V. / European Space Agency | British Library Conference Proceedings | 2011



    Separated flow region within a planar expansion-deflection nozzle.

    Hall, C. R., Jr. / Mueller, T. J. | NTRS | 1968