| タイトル | Transient Two-Dimensional Analysis of Side Load in Liquid Rocket Engine Nozzles |
| 本文（外部サイト） | http://hdl.handle.net/2060/20040085997 |
| 著者（英） | Wang, Ten-See |
| 著者所属（英） | NASA Marshall Space Flight Center |
| 発行日 | 2004-01-01 |
| 言語 | eng |
| 内容記述 | Two-dimensional planar and axisymmetric numerical investigations on the nozzle start-up side load physics were performed. The objective of this study is to develop a computational methodology to identify nozzle side load physics using simplified two-dimensional geometries, in order to come up with a computational strategy to eventually predict the three-dimensional side loads. The computational methodology is based on a multidimensional, finite-volume, viscous, chemically reacting, unstructured-grid, and pressure-based computational fluid dynamics formulation, and a transient inlet condition based on an engine system modeling. The side load physics captured in the low aspect-ratio, two-dimensional planar nozzle include the Coanda effect, afterburning wave, and the associated lip free-shock oscillation. Results of parametric studies indicate that equivalence ratio, combustion and ramp rate affect the side load physics. The side load physics inferred in the high aspect-ratio, axisymmetric nozzle study include the afterburning wave; transition from free-shock to restricted-shock separation, reverting back to free-shock separation, and transforming to restricted-shock separation again; and lip restricted-shock oscillation. The Mach disk loci and wall pressure history studies reconfirm that combustion and the associated thermodynamic properties affect the formation and duration of the asymmetric flow. |
| NASA分類 | Fluid Mechanics and Thermodynamics |
| レポートNO | AIAA Paper 2004-3680 |
| 権利 | No Copyright |
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