| タイトル | Reynolds Number and Leading-Edge Bluntness Effects on a 65 Deg Delta Wing |
| 本文（外部サイト） | http://hdl.handle.net/2060/20020016863 |
| 著者（英） | Luckring, J. M. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2002-01-01 |
| 言語 | eng |
| 内容記述 | A 65 deg delta wing has been tested in the National Transonic Facility (NTF) at mean aerodynamic chord Reynolds numbers from 6 million to 120 million at subsonic and transonic speeds. The configuration incorporated systematic variation of the leading edge bluntness. The analysis for this paper is focused on the Reynolds number and bluntness effects at subsonic speeds (M = 0.4) from this data set. The results show significant effects of both these parameters on the onset and progression of leading-edge vortex separation. |
| NASA分類 | Aerodynamics |
| レポートNO | AIAA Paper 2002-0419 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/92124 |
