| タイトル | Flight investigation of an air-cooled plug nozzle with afterburning turbojet |
| 本文（外部サイト） | http://hdl.handle.net/2060/19720024135 |
| 著者（英） | Samanich, N. E. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1972-09-01 |
| 言語 | eng |
| 内容記述 | A convectively cooled plug nozzle, using 4 percent of the engine air as the coolant, was tested in 1967 K (3540 R) temperature exhaust gas. No significant differences in cooling characteristics existed between flight and static results. At flight speeds above Mach 1.1, nozzle performance was improved by extending the outer shroud. Increasing engine power improved nozzle efficiency considerably more at Mach 1.2 than at 0.9. The effect of nozzle pressure ratio and secondary weight flow on nozzle performance are also presented. |
| NASA分類 | PROPULSION SYSTEMS |
| レポートNO | 72N31785
E-6676
NASA-TM-X-2607 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/202491 |
