| タイトル | Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.63 and 1.78, respectively, and with design pressure ratio of 1.82 |
| 本文（外部サイト） | http://hdl.handle.net/2060/19820011348 |
| 著者（英） | Moore, R. D.; Reid, L. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1982-02-01 |
| 言語 | eng |
| 内容記述 | The overall and blade-element performance of a transonic compressor stage is presented over the stable operating flow range for speeds from 50 to 100 percent of design. The stage was designed for a pressure ratio of 1.82 at a flow 20.2 kg/sec and a tip speed of 455 m/sec. At design speed the stage achieved a peak efficiency of 0.821 at a pressure ratio of 1.817. The stage stall margin at design speed based on conditions at stall and peak efficiency was about 11 percent. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 82N19222
E-259
NASA-TP-1974 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/166848 |
