| タイトル | Wind tunnel tests of a zero length, slotted-lip engine air inlet for a fixed nacelle V/STOL aircraft |
| 本文（外部サイト） | http://hdl.handle.net/2060/19830001749 |
| 著者（英） | Woollett, R. R.; Beck, W. E., Jr.; Glasgow, E. R. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1982-08-01 |
| 言語 | eng |
| 内容記述 | Zero length, slotted lip inlet performance and associated fan blade stresses were determined during model tests using a 20 inch diameter fan simulator in the NASA-LeRC 9 by 15 foot low speed wind tunnel. The model configuration variables consisted of inlet contraction ratio, slot width, circumferential extent of slot fillers, and length of a constant area section between the inlet throat and fan face. The inlet performance was dependent on slot gap width and relatively independent of inlet throat/fan face spacer length and slot flow blockage created by 90 degree slot fillers. Optimum performance was obtained at a slot gap width of 0.36 inch. The zero length, slotted lip inlet satisfied all critical low speed inlet operating requirements for fixed horizontal nacelles subsonic V/STOL aircraft. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 83N10019
NAS 1.15:82939
E-1338
NASA-TM-82939 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/164644 |
