Wind tunnel investigation was made at 0.60 to 1.40 Mach and jet total pressure ratios from 3 to 20; tested were 8° conical and 16° circular arc afterbody, and third afterbody having linear area variation with length; cylindrical afterbody was tested for comparison; extending from these bodies were 4 circular jet nozzles with design Mach number of 2.5, spaced symmetrically about body center line.
Effects of boattailing and nozzle extension on thrust-minus-drag of multiple-jet configuration
NASA -- Tech Note
1961
48 pages
Report
English
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Optimizing Exhaust — Nozzle/Airframe Thrust Minus Drag
SAE Technical Papers | 1968
|Optimizing exhaust -- Nozzle/airframe thrust minus drag
Engineering Index Backfile | 1968
|