| タイトル | Experiments on high bypass internal mixer nozzle jet noise |
| 本文（外部サイト） | http://hdl.handle.net/2060/19830007881 |
| 著者（英） | Goodykoontz, J. H. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1982-12-01 |
| 言語 | eng |
| 内容記述 | Model scale jet noise data are presented for a variety of internal lobed mixer nozzle configurations for take off power settings in a static environment. The results are presented for a 17.5 cm diameter fan nozzle to show the effect on noise levels caused by changes in geometric shape of the internal, or core flow, nozzle. The geometric variables include the lobe discharge angle, the number of lobes, spacing between the center plug and lobe valley, lobe side wall shape and axial contour of the lobes. An annular plug core flow nozzle was also tested and is used as a baseline for comparative purposes. Comparison of data from the internal lobed configurations showed that for comparative effect, in terms of the effect on full scale perceived noise levels, was caused by a change in the lobe discharge angle. The results showed that increasing the discharge angle caused an increase as large as 7 dB in sound pressure levels in the high frequency portion of the spectra. Changes in the other geometric variables cause negligible effects. |
| NASA分類 | ACOUSTICS |
| レポートNO | 83N16152
E-1456
NAS 1.15:83020
NASA-TM-83020 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/163805 |
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