| タイトル | Effect of exhaust nozzle configuration on aerodynamic and acoustic performance of an externally blown flap system with a quiet 6:1 bypass ratio engine |
| 本文（外部サイト） | http://hdl.handle.net/2060/19740001930 |
| 著者（英） | Heidelberg, L. J.; Samanich, N. E.; Jones, W. L. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1973-01-01 |
| 言語 | eng |
| 内容記述 | A highly suppressed TF-34 engine was used to investigate engine and flap interaction noise associated with an externally blown flap STOL powered lift system. Noise, efficiency, and velocity decay characteristics of mixed and separate flow exhaust systems including convergent, co-annular, and lobed designs were determined with the engine operating alone. Noise data were then obtained for several of the exhaust configurations with the engine blowing a wing-flap segment. Noise for both the engine alone and the engine with blown flaps showed substantial differences for the various exhaust configurations tested. The differences in observed noise are related primarily to nozzle effective exhaust velocity, flap impingement velocity, and noise spectral shape. |
| NASA分類 | AIRCRAFT |
| レポートNO | 74N10042
E-7765
NASA-TM-X-71466 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/197100 |
