| タイトル | Design of a very-low-bleed Mach 2.5 mixed-compression inlet with 45 percent internal contraction |
| 本文（外部サイト） | http://hdl.handle.net/2060/19750009291 |
| 著者（英） | Wasserbauer, J. F.; Shaw, R. J.; Neumann, H. E. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1975-03-01 |
| 言語 | eng |
| 内容記述 | A full-scale, mixed-compression inlet was designed for operation with the TF30-P-3 turbofan engine and tested at Mach numbers of 2.5 and 2.0. The two-cone axisymmetric inlet had minimum internal contraction consistent with high total pressure recovery and low cowl drag. At Mach 2.5, inlet recovery was 0.906 with only 0.021 centerbody bleed mass-flow ratio and no cowl bleed. Increased centerbody bleed gave a maximum inlet unstart angle of attack of 6.85 deg. At Mach 2.0, inlet recovery was 0.94 with only 0.014 centerbody bleed mass-flow ratio and no cowl bleed. Inlet performance and angle-of-attack tolerance is presented for operation at Mach numbers of 2.5 and 2.0. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 75N17363
E-8098
NASA-TM-X-3135 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/191054 |
