| タイトル | Computational Study of Flow Establishment in Hypersonic Pulse Facilities |
| 本文（外部サイト） | http://hdl.handle.net/2060/19960011378 |
| 著者（英） | Radhakrishnan, K.; Yungster, S. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1995-11-01 |
| 言語 | eng |
| 内容記述 | This paper presents a study of the temporal evolution of the combustion flowfield established by the interaction of ram-accelerator-type projectiles with an explosive gas mixture accelerated to hypersonic speeds in an expansion tube. The Navier-Stokes equations for a chemically reacting gas 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 (TVD) 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 expansion tube flowfields are then presented for two different configurations. In particular, the development of the shock-induced combustion process is followed. In one case, designed to ensure ignition only in the boundary layer, the lateral extent of the combustion front during the initial transient phase was surprisingly large. The time histories of the calculated thrust and drag forces on the ram accelerator projectile are also presented. |
| NASA分類 | FLUID MECHANICS AND HEAT TRANSFER |
| レポートNO | 96N17814
NASA-CR-198407
NAS 1.26:198407
E-9930
ICOMP-95-19
NIPS-96-07535 |
| 権利 | Copyright, Distribution under U.S. Government purpose rights |
