| タイトル | Fluidic Thrust Vectoring of an Axisymmetric Exhaust Nozzle at Static Conditions |
| 本文（外部サイト） | http://hdl.handle.net/2060/20040110397 |
| 著者（英） | Wing, David J.; Giuliano, Victor J. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1997-01-01 |
| 言語 | eng |
| 内容記述 | A sub-scale experimental static investigation of an axisymmetric nozzle with fluidic injection for thrust vectoring was conducted at the NASA Langley Jet Exit Test Facility. Fluidic injection was introduced through flush-mounted injection ports in the divergent section. Geometric variables included injection-port geometry and location. Test conditions included a range of nozzle pressure ratios from 2 to 10 and a range of injection total pressure ratio from no-flow to 1.5. The results indicate that fluidic injection in an axisymmetric nozzle operating at design conditions produced significant thrust-vector angles with less reduction in thrust efficiency than that of a fluidically-vectored rectangular jet. The axisymmetric geometry promoted a pressure relief mechanism around the injection slot, thereby reducing the strength of the oblique shock and the losses associated with it. Injection port geometry had minimal effect on thrust vectoring. |
| NASA分類 | Aircraft Design, Testing and Performance |
| レポートNO | DWSAM97-3228 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/88175 |
