| タイトル | Experimental Evaluation of Turning Vane Designs for High-speed and Coupled Fan-drive Corners of 0.1-scale Model of NASA Lewis Research Center's Proposed Altitude Wind Tunnel |
| 本文（外部サイト） | http://hdl.handle.net/2060/19880008302 |
| 著者（英） | Boldman, Donald R.; Shyne, Rickey J.; Moore, Royce D.; Gelder, Thomas F. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1987-05-01 |
| 言語 | eng |
| 内容記述 | Two turning vane designs were experimentally evaluated for the fan-drive corner (corner 2) coupled to an upstream diffuser and the high-speed corner (corner 1) of the 0.1 scale model of NASA Lewis Research Center's proposed Altitude Wind Tunnel. For corner 2 both a controlled-diffusion vane design (vane A4) and a circular-arc vane design (vane B) were studied. The corner 2 total pressure loss coefficient was about 0.12 with either vane design. This was about 25 percent less loss than when corner 2 was tested alone. Although the vane A4 design has the advantage of 20 percent fewer vanes than the vane B design, its vane shape is more complex. The effects of simulated inlet flow distortion on the overall losses for corner 1 or 2 were small. |
| NASA分類 | RESEARCH AND SUPPORT FACILITIES (AIR) |
| レポートNO | 88N17686
NAS 1.60:2681
E-3218
NASA-TP-2681 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/82890 |
