Effect of Tabs on the Thrust of a Convergent Nozzle
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摘要: 针对收敛喷管,在近临界状态及超临界状态下,实验研究了加装小突片后对飞机发动机尾喷管推力特性的影响,并探讨了小突片堵塞比、小突片后倾角度,以及片数等因素的作用.结果表明,小突片对收敛喷管的推力特性有明显的影响,并且小突片所造成的推力损失基本上随小突片的堵塞比增加而增加.在实验范围内,小突片堵塞比每增加1%,所造成的推力损失在0.63%~1.35%之间,对超临界状态,可认为大约增加0.8%.Abstract: An experimental investigation on the effect of tabs, which is fixed on the exit of a convergent nozzle, to thrust characteristics has been conducted at both subcritical and supercritical flow conditions. The variable parameters of tabs are block ratio, inclined angle and the number of tabs. The experimental results show that the tabs indeed cause thrust loss, and the thrust loss will increase with the block ratio of tabs. Within the test range of the experiments, the thrust loss is between 0.65%~1.35% per 1% tab block ratio, and especially about 0.8% per 1% at supercritical flow condition.
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Key words:
- convergent nozzles /
- propelling nozzle characteristics /
- mixing flow /
- tabs
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