| タイトル | Numerical investigation of supersonic turbulent boundary layers with high wall temperature |
| 本文（外部サイト） | http://hdl.handle.net/2060/19950014633 |
| 著者（英） | Guo, Y.; Adams, N. A. |
| 著者所属（英） | Deutsche Forschungsanstalt fuer Luft- und Raumfahrt |
| 発行日 | 1994-12-01 |
| 言語 | eng |
| 内容記述 | A direct numerical approach has been developed to simulate supersonic turbulent boundary layers. The mean flow quantities are obtained by solving the parabolized Reynolds-averaged Navier-Stokes equations (globally). Fluctuating quantities are computed locally with a temporal direct numerical simulation approach, in which nonparallel effects of boundary layers are partially modeled. Preliminary numerical results obtained at the free-stream Mach numbers 3, 4.5, and 6 with hot-wall conditions are presented. Approximately 5 million grid points are used in all three cases. The numerical results indicate that compressibility effects on turbulent kinetic energy, in terms of dilatational dissipation and pressure-dilatation correlation, are small. Due to the hot-wall conditions the results show significant low Reynolds number effects and large streamwise streaks. Further simulations with a bigger computational box or a cold-wall condition are desirable. |
| NASA分類 | FLUID MECHANICS AND HEAT TRANSFER |
| レポートNO | 95N21050 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/108541 |
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