Rui LI, Jinglei XU, Haiyin LV

DOI Number: 10.82241/ceas-hisst-2024-285

Conference number: HiSST–2024-285

This study numerically investigates the performance of supersonic splitline nozzles concerning interactions between the airflow and the particles of aluminum trioxide. The existence of the initial arc radius concentrates heavy particles along the axis and scatters light particles to the nozzle transition region. The total length influences the shock wave reflections in the nozzle. The convex diverging profile with a large secondary radius is beneficial for balancing performance parameters. In addition, the swing
center upstream of the throat can enlarge the lateral force. Based on these recognitions, the nozzle configuration with an initial arc radius of 10 mm, a total nozzle length of 50 mm, a convex secondary arc of 200 mm, and a swing center at the throat is finally selected to obtain the optimal aerodynamic performance. With the increase in the swing angle from 0 to 6°, the thrust coefficient only drops by 1.89% and always keeps above 0.9356. Meanwhile, its amplification factor exceeds 1.302, and its maximum thrust vector angle is 7.796°

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In Categories: 1.Events, HiSST 2024, Propulsion Systems and Components
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