| タイトル | A computational investigation of mixing and reacting flows in supersonic combustors |
| 著者（英） | Riggins, D. W.; Mcclinton, C. R. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1992-01-01 |
| 言語 | eng |
| 内容記述 | Results of the numerical simulation of 15 degree downstream helium injection into a unconfined Mach 6 airstream are presented. Both details of downstream mixing and mean flow are in good agreement with experimental data. Results of the numerical simulation of similar hydrogen injection into a high enthalpy (Mach 17) confined Mach 6 airstream are presented with favorable comparison to experimental plume structure and wall data. The low enthalpy inflow from the unconfined case was then provided to the high enthalpy geometry in order to study the feasibility of using low enthalpy simulations of mixing for scramjet flight performance estimation. Results indicate that the mixing is substantially lower for the high enthalpy case but can be shown to appropriately scale using the inflow velocity. Production and decay of axial vorticity, cross-flow velocities, and the mean-flow velocities of these confined flows are then related and discussed to illustrate the effect of residence time on jet mixing. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 92A23817
AIAA PAPER 92-0626 |
| 権利 | Copyright |
