Abstract
Experiments are conducted on a supersonic mixing layer with two lobed mixers, which are designed following the concept of a shock-eliminating combustor. Instantaneous images were obtained to examine the evolution process of large-scale vortices downstream of the lobed mixers. The results show that no streamwise vortices appeared downstream of the lobed mixer with a penetration angle of approximately 6.7° owing to the smaller pressure difference between the peak and trough regions of the lobed mixer compared with the rectangular lobed mixer (RLM). However, it provides a similar mixing enhancement as an RLM. Streamwise vortices appear downstream of the lobed mixer with a higher penetration angle of approximately 9.7°. Greater mixing enhancement is observed in the lobed mixer with a larger penetration angle. The lobed mixers have potential applications for mixing enhancement in air-breathing propulsion systems, such as scramjet engines.
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