利用边条涡抑制Y形进气道流场畸变  

USING STRAKE VORTEX TO REDUCE THE DISTORTION OF A Y SHAPED INLET

作　　者：黄国平[1] 杨德华 梁德旺[1] 李博[1] 

机构地区：[1]南京航空航天大学204教研室,江苏南京210016 [2]贵州航空工业集团飞机设计所,贵州安顺561000

出　　处：《航空学报》2000年第2期113-117,共5页Acta Aeronautica et Astronautica Sinica

摘　　要：已用于飞机外流流场控制的边条涡技术被首次引入内流场的控制 ,抑制进气道出口流场畸变 ,改善进发匹配。针对某型飞机的 Y形进气道 ,有 3对边条涡片被加装在进气道内 ,与通常的涡流发生器不同的是 ,这些涡片被设计来控制整个进气道流场而不是仅仅改善局部的附面层。大量的实验结果证实 ,这种流场控制措施的改善效果显著 ,某型飞机的 Y形进气道在亚、跨和超声速等各种飞行速度 ,及不同攻角、侧滑角和开关放气门等飞行条件下 ,其出口流场畸变均减小 ,尤其是原流场畸变较大的情况下改善更加明显。The technology of strake wings that has been applied to control external flows was employed firstly in the control of internal flows in this paper, in order to reduce the distortion of a Y\|shaped inlet and improve the inlet\|engine compatibility. Three couples of strake wings were installed in the inlet. Unlike the ordinary vortex generator, these strake wings were designed to control not only the local boundary layer but also the whole flow field. Results of a lot of experiments showed that the flow controller consisting of strake wings is effective to improve the inlet\|engine compatibility. The distortions of the Y\|shaped inlet with the controller under various conditions, such as subsonic, transonic and supersonic flying velocity; various attack angles, yaw angles and opening angles of an auxiliary inlet, are greatly reduced, especially for the cases that the original distortions are serious.

关 键 词：压力畸变 边条涡 Y形进气道 飞机 内流场控制 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]