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Cold-flow acoustic evaluation of a small scale, divergent, lobed nozzle for supersonic jet noise suppression
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Groesbeck, D. E. Huff, R. G. |
| Copyright Year | 1975 |
| Description | A supersonic jet noise suppressor was tested with cold flow for acoustic and thrust characteristics at nozzle- to atmospheric-pressure ratios of 1.5 to 4.0. Jet noise suppression and spectral characteristics of the divergent, lobed, suppressor (DLS) nozzle with and without an ejector are presented. Suppression was obtained at nozzle pressure ratios of 2.5 to 4.0. The largest, maximum-lobe, sound pressure level suppression with a hard-wall ejector was 14.6 decibels at a nozzle pressure ratio of 3.5. The thrust loss was 2 percent. In general, low-frequency jet noise was suppressed, leaving higher frequencies essentially unchanged. Without the ejector the nozzle showed a thrust loss of 11 percent together with slightly poorer noise suppression. |
| File Size | 1618774 |
| Page Count | 41 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19750010902 |
| Archival Resource Key | ark:/13960/t5v746r25 |
| Language | English |
| Publisher Date | 1975-03-01 |
| Access Restriction | Open |
| Subject Keyword | Acoustics Supersonic Aircraft Jet Aircraft Noise Noise Reduction Supersonic Nozzles Noise Spectra Suppressors Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
