| タイトル | Computational Study of Flow Establishment in a Ram Accelerator |
| 本文（外部サイト） | http://hdl.handle.net/2060/19960009096 |
| 著者（英） | Radhakrishnan, K.; Yungster, S.; Rabinowitz, M. J. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1995-11-01 |
| 言語 | eng |
| 内容記述 | The temporal evolution of the combustion process established during projectile transition from the launch tube into the ram accelerator section containing an explosive hydrogen-oxygen-argon gas mixture is studied. The Navier-Stokes equations for chemically reacting flow are solved in a fully coupled manner, using an implicit, time accurate algorithm. The solution procedure is based on a spatially second order total variation diminishing scheme and a temporally second order, variable-step, backward differentiation formula method. The hydrogen-oxygen chemistry is modeled with a 9-species, 19-step mechanism. The accuracy of the solution method is first demonstrated by several benchmark calculations. Numerical simulations of two ram accelerator configurations are then presented. In particular, the temporal developments of shock-induced combustion and thrust forces are followed. Positive thrust is established in both cases; however, in one of the ram accelerator configurations studied, combustion in the boundary layer enhances its separation, ultimately resulting in unstart. |
| NASA分類 | FLUID MECHANICS AND HEAT TRANSFER |
| レポートNO | 96N16262
NASA-TM-107068
NAS 1.15:107068
E-9931
ICOMP-95-20
AIAA PAPER 95-2489
NIPS-95-06486 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
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