| タイトル | Operating characteristics of an inlet model tested with a 0.5m powered fan at high angles of attack |
| 本文（外部サイト） | http://hdl.handle.net/2060/19770024152 |
| 著者（英） | Koncsek, J. L.; Shaw, R. J. |
| 著者所属（英） | Boeing Co.|NASA Lewis Research Center |
| 発行日 | 1977-09-01 |
| 言語 | eng |
| 内容記述 | An inlet model designed for high angle of attack capability, coupled to a .508 m tip diameter turbofan simulator, was tested in the NASA-Lewis Research Center's 9-by 15-ft low speed wind tunnel. The test variables were: tunnel velocity, 0 to 75 m/s; inlet angle of attack, 0 to 120 deg; and fan face corrected airflow per unit area, 75 to 200 kg/s sqm. The inlet flow separation boundaries, the fan face total pressure recovery and distortion characteristics, and the fan blade vibratory stresses were determined. The recovery, distortion, and stress levels showed no abrupt changes at the onset of separation, but became gradually more unfavorable as the size and intensity of the separation increased as induced by increasingly severe operating conditions. Performance characteristics for a large scale model of the inlet were estimated from these test results. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 77N31096
D180-20798-1
NASA-CR-135270 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/181339 |
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