| タイトル | Zero-length inlets for subsonic V/STOL aircraft |
| 著者（英） | Glasgow, E. R.; Woollett, R. R.; Beck, W. E. |
| 著者所属（英） | Lockheed-California Co.|NASA Lewis Research Center |
| 発行日 | 1981-07-01 |
| 言語 | eng |
| 内容記述 | Zero-length inlet performance and associated fan blade stresses were determined during model tests in the NASA-LeRC 9-by 15-foot low-speed wind tunnel. The inlet models, which were installed on a 20-inch diameter fan unit, had different inlet lip contraction ratios as well as unslotted, slotted, and double slotted inlet lips. The inlet angle-of-attack boundaries for onset of flow separation were identified and compared to the operating requirements of several generically different subsonic V/STOL aircraft. The zero-length inlets, especially those with slotted lips, were able to satisfy these requirements without compromising the maximum cowl forebody radius. As an aid to the inlet design process, a unique relationship was established between the maximum surface Mach number associated with the separation boundary and the maximum-to-throat surface velocity ratio. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 81A42186
AIAA PAPER 81-1396 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/415780 |
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