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An Experimental Study of Clustered, Two-Dimensional Rocket Nozzles.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
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This thesis is about the construction and employment of hardware for investigating the pressure fields and flow phenomena in the base region of clustered nozzles during cold flow testing. Ambient test conditions simulating altitudes up to 75,000 feet and chamber to ambient pressure ratios up to 200 can be established. The clusters considered were made up of a pair of two-dimensional supersonic convergent divergent nozzles with a design exit Mach number of 3.68. Three nozzle sets were studied each having different spacing between the nozzles. A Schilieren system that allowed for both still photographs and film was used to supplement the pressure data. This study indicates that the pressure fields in the base region of a nozzle cluster are heavily dependent on both geometry and on the operating altitude. The outer wall of the test section adjacent to the nozzles was observed to significantly affect the flow patterns and measured pressures. Potential influences on performance exist due both to changes in the gas dynamics of the flow and the appearance of additional pressure-area terms. Keywords include Rocket nozzles, and Nozzle clusters.
APPROVED FOR PUBLIC RELEASE