| タイトル | Experimental evaluation of corner turning vanes |
| 本文（外部サイト） | http://hdl.handle.net/2060/19870019138 |
| 著者（英） | Shyne, Rickey J.; Gelder, Thomas F.; Boldman, Donald R.; Moore, Royce D. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1987-01-01 |
| 言語 | eng |
| 内容記述 | Two types of turning vane airfoils (a controlled-diffusion shape and a circular arc shape) have been evaluated in the high-speed and fan-drive corners of a 0.1-scale model of NASA Lewis Research Center's proposed Altitude Wind Tunnel. The high-speed corner was evaluated with and without a simulated engine exhaust removal scoop. The fan-drive corner was evaluated with and without the high-speed corner. Flow surveys of pressure and flow angle were taken for both the corners and the vanes to determine their respective losses. The two-dimensional vane losses were low; however, the overall corner losses were higher because three-dimensional flow was generated by the complex geometry resulting from the turning vanes intersecting the end wall. The three-dimensional effects were especially pronounced in the outer region of the circular corner. |
| NASA分類 | RESEARCH AND SUPPORT FACILITIES (AIR) |
| レポートNO | 87N28571
NASA-TM-100143
E-3695
NAS 1.15:100143 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/149041 |
