Abstract
The mean velocity and turbulence quantities in simulated two-dimensional (2-D) and three-dimensional (3-D) solid-propellant ducted rocket (SDR) combustor flow fields were measured using a two-component laser-Doppler velocimetry system. The Reynolds number, based on the combustor height and bulk mean velocity and momentum ratio of the axial inlet to side inlets were 4.56 × 10 4 and 0.11, respectively, for the 2-D flow field and 5.92 × 10 4 and 0.20 for the 3-D flow field. It is found that the well-organized dome vortices and separating bubbles in the 2-D flow are absent in the 3-D flow. To provide a reference for turbulence modeling, the 2-D flow is also characterized in terms of turbulent structure parameter. In addition, the penetration of the axial jet through the side-inlet jets and the mixing of the axial-inlet with the side-inlet streams are documented.
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