| タイトル | Acoustic, performance, and wake survey measurements of a lobed velocity-decayer nozzle installed on a quieted TF-34 turbofan engine |
| 本文（外部サイト） | http://hdl.handle.net/2060/19760023128 |
| 著者（英） | Heidelberg, L. J.; Samanich, N. E. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1976-08-01 |
| 言語 | eng |
| 内容記述 | Results for three velocity decayer nozzle configurations are compared with those obtained with a separate flow coannular nozzle tested on the same quieted turbofan engine. Peak sideline noise, which occurred 110 degrees from the inlet, was 2 to 4 db louder than with the coannular nozzle at the same ideal effective exhaust velocity and 8 to 11 db louder at the same thrust level. The decayer nozzles produced an increase in loss equivalent to about 4 percent of the engine thrust and also increased the effective exhaust velocity of the engine. The exhaust decayed to 0.35 of its peak velocity, compared with no decay for the coannular nozzle, within 3 equivalent nozzle diameters of the exit. The peak exhaust gas temperature was 400 K lower for the decayer configuration at the same location. The increase in perceived noise level for the decayer nozzles as compared with the coannular nozzle was attributed to the increase in exhaust velocity and the shift in peak spectrum frequency produced by these nozzles. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 76N30216
E-8676
NASA-TM-X-3413 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/184830 |
