NASA NTRS · 19720010364
Mixer nozzle-externally blown flap noise tests
Abstract
A summary is given of the noise suppression tests conducted for the STOL aircraft. The tests were made using a large scale mixer nozzle and externally blown flap model. Data were obtained over a range of nozzle exhaust velocities (172 to 284 m/sec) and flap angles. Comparisons were made between the results of the mixer nozzle and those obtained with a standard single convergent nozzle. The resulting conclusions show that a reduction in noise level did occur using the mixer nozzle system.
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Goodykoontz, J. H., Dorsch, R. G., Groesbeck, D. E.. 1972-02-01. Mixer nozzle-externally blown flap noise tests. https://ntrs.nasa.gov/citations/19720010364
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