小突片对收敛喷管推力特性的影响研究  

Effect of Tabs on the Thrust of a Convergent Nozzle

作　　者：黄勇[1] 郭志辉[1] 魏福清[1] 吴寿生[1] 

机构地区：[1]北京航空航天大学动力系

出　　处：《北京航空航天大学学报》2001年第6期687-689,共3页Journal of Beijing University of Aeronautics and Astronautics

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 6 3 %～ 1 3 5 %之间 ,对超临界状态 ,可认为大约增加 0 8% .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.

关 键 词：收敛喷管 推力喷管特性 混合流动 小突片 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]