| タイトル | Hypersonic Boundary-Layer Trip Development for Hyper-X |
| 本文（外部サイト） | http://hdl.handle.net/2060/20000080347 |
| 著者（英） | Auslender, Aaron H.; Calleja, John F.; Dilley, Authur D.; Berry, Scott A. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2000-08-10 |
| 言語 | eng |
| 内容記述 | Boundary layer trip devices for the Hper-X forebody have been experimentally examined in several wind tunnels. Five different trip configurations were compared in three hypersonic facilities, the LaRC 20-Inch Mach 6 Air Tunnel, the LaRC 31 -Inch Mach 10 Air Tunnel, and in the HYPULSE Reflected Shock Tunnel at GASL. Heat transfer distributions, utilizing the phosphor thermography and thin-film techniques, shock system details, and surface streamline patterns were measured on a 0.333-scale model of the Hyper-X forebody. Parametric variations include angles-of-attack of 0-deg, 2-deg, and 4-deg; Reynolds numbers based on model length of 1.2 to 15.4 million: and inlet cowl door simulated in both open and closed positions. Comparisons of transition due to discrete roughness elements have led to the selection of a trip configuration for the Hyper-X Mach 7 flight vehicle. |
| NASA分類 | Aerodynamics |
| レポートNO | AIAA Paper 2000-4012 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/94180 |
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