| タイトル | Characterization of supersonic mixing in a nonreacting Mach 2 combustor |
| 著者（英） | Hartfield, Roy J., Jr.; Mcdaniel, James C.; Hollo, Steven D. |
| 著者所属（英） | Virginia Univ. |
| 発行日 | 1992-01-01 |
| 言語 | eng |
| 内容記述 | Planar measurements of the injection mole fraction distribution and the velocity field within a nonreacting model SCRAMJET combustor have been made using laser-induced iodine fluorescence. The combustor geometry investigated in this work is staged transverse injection of air into a Mach 2 freestream. A complete three-dimensional survey of the injectant mole fraction distribution has been generated and a single planar velocity measurement has been completed. The measurements reveal the dramatic effect of streamwise vortices on the mixing of the injectant in the near field of the injectors, as well as the rapid mixing generated by staging two field injectors. Analysis of the downstream decay of the maximum injectant mole fraction in this and other nonreacting combustor geometries indicates that the relative rate of injectant mixing well downstream of the injectors is independent of combustor geometry, combustor Mach number, and injectant molecular weight. Mixing within this region of the combustor is dominated by turbulent diffusion within the injectant plume. The transition of the dominant mixing mechanism, from vortex-driven mixing in the near field to turbulent diffusion in the far field, was found to occur in the region between 10 and 20 jet diameters downstream of the injectors. |
| NASA分類 | FLUID MECHANICS AND HEAT TRANSFER |
| レポートNO | 92A22199
AIAA PAPER 92-0093 |
| 権利 | Copyright |
|
