| タイトル | Thrust-augmented vortex attenuation |
| 本文（外部サイト） | http://hdl.handle.net/2060/19780004081 |
| 著者（英） | Patterson, J. C., Jr.; Jordan, F. L., Jr. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1977-01-01 |
| 言語 | eng |
| 内容記述 | An experimental investigation was conducted to determine the vortex attenuating effect of engine thrust. Tests were made using a 0.03-scale model of the Boeing 747 transport aircraft as a vortex generating model. A Learjet-class probe model was used to measure the vortex induced rolling moment at a scale separation distance of 1.63 km. These tests were conducted at a lift coefficient of 1.4 at a model velocity of 30.48 m/s. The data presented indicate that engine thrust is effective as a vortex attenuating device when the engines are operated at high thrust levels and are positioned to direct the high energy engine wake into the core of the vortex. The greatest thrust vortex attenuation was obtained by operating the inboard engine thrust reversers at one-quarter thrust and the outboard engines at maximum forward thrust. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 78N12024 |
| 権利 | No Copyright |
