To obtain data on suppressor nozzles considered for aircraft jet transport, one-fifth scale suppressors are tested at Mach numbers from 0.65 to 1.10 over range of nozzle pressure ratios and total and component drag coefficients presented; drag increases due to suppressors presented in terms of net thrust; propulsive thrust losses calculated, and results converted into aircraft payload penalty; least drag was caused by lobe type suppressor.
Transonic drag of several jet-noise suppressors
NACA -- Tech Note
NACA -- Technical Note ; n 4269
1958
34 pages
Report
English
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Transonic Drag of Several Jet-noise Suppressors
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