| タイトル | A Combined Experimental/Computational Investigation of a Rocket Based Combined Cycle Inlet |
| 本文（外部サイト） | http://hdl.handle.net/2060/20010023936 |
| 著者（英） | Smart, Michael K.; Trexler, Carl A.; Goldman, Allen L. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2001-01-01 |
| 言語 | eng |
| 内容記述 | A rocket based combined cycle inlet geometry has undergone wind tunnel testing and computational analysis with Mach 4 flow at the inlet face. Performance parameters obtained from the wind tunnel tests were the mass capture, the maximum back-pressure, and the self-starting characteristics of the inlet. The CFD analysis supplied a confirmation of the mass capture, the inlet efficiency and the details of the flowfield structure. Physical parameters varied during the test program were cowl geometry, cowl position, body-side bleed magnitude and ingested boundary layer thickness. An optimum configuration was determined for the inlet as a result of this work. |
| NASA分類 | Spacecraft Propulsion and Power |
| レポートNO | AIAA Paper 2001-0671 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/93277 |
