Abstract

Appearance of so-called restricted shock(-induced) flow separation (RSS) in nozzle has been revealed experimentally in a high-area-ratio model nozzle with a truncated ideal contour (TIC) and a back cone at its exit for facilitating liquid rocket engines (LRE) ground tests with such nozzles. As a result, conditions of transition from so-called free shock(- induced) flow separation (FSS) to RSS in this nozzle with the exit back cone of different exit diameter during the chamber pressure rise and vice versa during its reduction has been investigated. In addition an analysis of pressure pulsations in the flow separation region and oil pictures on the inner nozzle surface both in the nozzle with the exit back cone and without it have allowed us to clear the RSS flow pattern.

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