| タイトル | A pressure flux-split technique for computation of inlet flow behavior |
| 本文（外部サイト） | http://hdl.handle.net/2060/19910011755 |
| 著者（英） | Rubin, S. G.; Pordal, H. S.; Khosla, P. K. |
| 著者所属（英） | Cincinnati Univ. |
| 発行日 | 1991-01-01 |
| 言語 | eng |
| 内容記述 | A method for calculating the flow field in aircraft engine inlets is presented. The phenomena of inlet unstart and restart are investigated. Solutions of the reduced Navier-Stokes (RNS) equations are obtained with a time consistent direct sparse matrix solver that computes the transient flow field both internal and external to the inlet. Time varying shocks and time varying recirculation regions can be efficiently analyzed. The code is quite general and is suitable for the computation of flow for a wide variety of geometries and over a wide range of Mach and Reynolds numbers. |
| NASA分類 | FLUID MECHANICS AND HEAT TRANSFER |
| レポートNO | 91N21068 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/133311 |
