| タイトル | Computational Analysis of a Low-Boom Supersonic Inlet |
| 本文（外部サイト） | http://hdl.handle.net/2060/20110023757 |
| 著者（英） | Chima, Rodrick V. |
| 著者所属（英） | NASA Glenn Research Center |
| 発行日 | 2011-11-01 |
| 言語 | eng |
| 内容記述 | A low-boom supersonic inlet was designed for use on a conceptual small supersonic aircraft that would cruise with an over-wing Mach number of 1.7. The inlet was designed to minimize external overpressures, and used a novel bypass duct to divert the highest shock losses around the engine. The Wind-US CFD code was used to predict the effects of capture ratio, struts, bypass design, and angles of attack on inlet performance. The inlet was tested in the 8-ft by 6-ft Supersonic Wind Tunnel at NASA Glenn Research Center. Test results showed that the inlet had excellent performance, with capture ratios near one, a peak core total pressure recovery of 96 percent, and a stable operating range much larger than that of an engine. Predictions generally compared very well with the experimental data, and were used to help interpret some of the experimental results. |
| NASA分類 | Aircraft Propulsion and Power |
| レポートNO | AIAA Paper 2011-3801
E-17906
NASA/TM-2011-217223 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/244557 |
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