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This document summarizes an experimental study that directly compared the performance of a standard conical nozzle and a bell nozzle optimized for maximum thrust using the Rao method on two small rocket engines with 110N of thrust. Testing was conducted at two different fuel film cooling percentages and three different chamber pressures on the two nozzles, which had throat Reynolds numbers ranging from 2x104 to 4x104. The results showed that for this Reynolds number range, the bell nozzle outperformed the c

Author

Bill M. Sprague

Language

EN