| タイトル | Design and Predictions for High-Altitude (Low Reynolds Number) Aerodynamic Flight Experiment |
| 本文（外部サイト） | http://hdl.handle.net/2060/20000095076 |
| 著者（英） | Drela, Mark; Greer, Donald; Harmory, Phil; Krake, Keith |
| 著者所属（英） | NASA Dryden Flight Research Center |
| 発行日 | 2000-08-01 |
| 言語 | eng |
| 内容記述 | A sailplane being developed at NASA Dryden Flight Research Center will support a high-altitude flight experiment. The experiment will measure the performance parameters or an airfoil at high altitudes (70,000 - 100,000 ft), low Reynolds numbers (2 x 10(exp 5) - 7 x 10(exp 5)), and high subsonic Mach numbers (0.5 and 0.65). The airfoil section lift and drag are determined from pilot and static pressure measurements. The locations of the separation bubble, Tollmien-Schlichting boundary-layer instability frequencies, and vortex shedding are measured from a hot-film strip. The details of the planned flight experiment are presented as well as several predictions of the airfoil performance. |
| NASA分類 | Aircraft Design, Testing and Performance |
| 権利 | Copyright, Distribution as joint owner in the copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/93991 |
