Results indicate that performance of combinations was little affected by sonic or supersonic base bleed; efficiency of terminal-fairing model, designed to improve performance of fixed geometry nozzle at transonic speeds, was only about 3 to 5% less than those of convergent divergent nozzles.
Effect of base bleed and terminal fairings on performance of exhaust-nozzle-afterbody combinations at mach numbers of 1.93, 2.55, and 3.05
NASA -- Tech Note
1960
31 pages
Report
Englisch
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