| タイトル | Distortion in a full-scale bicone inlet with internal focused compression and 45 percent internal contraction |
| 本文（外部サイト） | http://hdl.handle.net/2060/19750003898 |
| 著者（英） | Neumann, H. E.; Wasserbauer, J. F.; Shaw, R. J. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1974-12-01 |
| 言語 | eng |
| 内容記述 | The distortion characteristics were investigated at the subsonic diffuser exit of a full-scale, Mach 2.5, axisymmetric, mixed compression inlet. Performance and steady-state distortion characteristics were obtained at zero and maximum angle of attack and during an inlet unstart-restart sequence. For the configuration with no cowl bleed, steady-state distortion P(max)P(min)P(bar) ranged from 0.10 for critical inlet operation at 0 deg angle-of-attack to 0.306 for supercritical inlet operation at 6.84 deg angle-of-attack. Vortex generators provided a 50 percent reduction in steady-state distortion for critical operation. Bleed has a smaller effect on steady-stated distortion. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 75N11970
NASA-TM-X-3133
E-7992 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/192132 |
