| タイトル | Secondary flow spanwise deviation model for the stators of NASA middle compressor stages |
| 本文（外部サイト） | http://hdl.handle.net/2060/19840010134 |
| 著者（英） | Sandercock, D. M.; Roberts, W. B. |
| 著者所属（英） | Santa Clara Univ. |
| 発行日 | 1984-02-01 |
| 言語 | eng |
| 内容記述 | A model of the spanwise variation of deviation for stator blades is presented. Deviation is defined as the difference between the passage mean flow angle and the metal angle at the outlet of a blade element of an axial compressor stage. The variation of deviation is taken as the difference above or below that predicted by blade element, (i.e., two-dimensional) theory at any spanwise location. The variation of deviation is dependent upon the blade camber, solidity and inlet boundary layer thickness at the hub or tip end-wall, and the blade channel aspect ratio. If these parameters are known or can be calculated, the model provides a reasonable approximation of the spanwise variation of deviation for most compressor middle stage stators operating at subsonic inlet Mach numbers. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 84N18202
NAS 1.26:173360
NASA-CR-173360 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/160265 |
