| タイトル | Compressibility Considerations for kappa-omega Turbulence Models in Hypersonic Boundary Layer Applications |
| 本文（外部サイト） | http://hdl.handle.net/2060/20090015399 |
| 著者（英） | Rumsey, C. L. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2009-04-01 |
| 言語 | eng |
| 内容記述 | The ability of kappa-omega models to predict compressible turbulent skin friction in hypersonic boundary layers is investigated. Although uncorrected two-equation models can agree well with correlations for hot-wall cases, they tend to perform progressively worse - particularly for cold walls - as the Mach number is increased in the hypersonic regime. Simple algebraic models such as Baldwin-Lomax perform better compared to experiments and correlations in these circumstances. Many of the compressibility corrections described in the literature are summarized here. These include corrections that have only a small influence for kappa-omega models, or that apply only in specific circumstances. The most widely-used general corrections were designed for use with jet or mixing-layer free shear flows. A less well-known dilatation-dissipation correction intended for boundary layer flows is also tested, and is shown to agree reasonably well with the Baldwin-Lomax model at cold-wall conditions. It exhibits a less dramatic influence than the free shear type of correction. There is clearly a need for improved understanding and better overall physical modeling for turbulence models applied to hypersonic boundary layer flows. |
| NASA分類 | Aeronautics (General) |
| レポートNO | LF99-8457
L-19589
NASA/TM-2009-215705 |
| 権利 | No Copyright |
