Wind tunnel investigation to determine effect on thrust for nozzle overexpansion of cylindrical afterbody with single nozzle such as used in rocket engines was conducted at Mach numbers from 0.9 to 1. 4; results indicated that proper balance between nozzle overexpansion and base area exists, which will produce maximum afterbody net thrust factor over given operating range.
Effect on thrust minus base drag of exchanging base area for nozzle expansion in supersonic nozzles at transonic Mach numbers
NASA -- Tech Note
1961
30 pages
Report
English
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