| タイトル | Transonic Reynolds Number and Leading-Edge Bluntness Effects on a 65 deg Delta Wing |
| 本文（外部サイト） | http://hdl.handle.net/2060/20040139861 |
| 著者（英） | Luckring, J. M. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2003-01-01 |
| 言語 | eng |
| 内容記述 | A 65 degree 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 a systematic variation of the leading edge bluntness. The analysis for this paper is focused on the Reynolds number and bluntness effects at transonic speeds (M = 0.85) 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 | Aircraft Design, Testing and Performance |
| レポートNO | AIAA Paper 2003-0753 |
| 権利 | No Copyright |
