| タイトル | Gust Generator for a Supersonic Wind Tunnel |
| 本文（外部サイト） | http://hdl.handle.net/2060/19750004898 |
| 著者（英） | Bishop, Allan R.; Webb, John A., Jr.; Sanders, Bobby W. |
| 発行日 | 1974-12-01 |
| 言語 | eng |
| 内容記述 | The effectiveness was investigated of a flat plate gust generator that was located in the nozzle throat of the Lewis 10- by 10-foot supersonic wind tunnel. Gust plates were tested at nozzle wall Mach numbers of 3.1, 2.4, and 2.0. Test results show that the flat plate concept may be used as a gust generator for a wind tunnel; however, more extensive investigation is required to completely define its capabilities and limitations. For the single transient data point recorded, a gust amplitude (decrement) of 0.15 in Mach number was obtained. Analysis of these transient data indicates a response with a corner frequency of at least 8 hertz. |
| NASA分類 | RESEARCH AND SUPPORT FACILITIES (AIR) |
| レポートNO | 75N12970
NASA-TM-X-3120
E-7978 |
| 権利 | No Copyright |
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