头部厚度分布对飞翼布局失速特性影响研究  

Effect of nose thickness distribution on the stall characteristics of low aspect ratio flying wing configuration at transonic flow

作　　者：单继祥[1] 黄勇[2] 张旭 

机构地区：[1]中国工程物理研究院总体工程研究所,绵阳621999 [2]中国空气动力研究与发展中心高速空气动力研究所,绵阳621000

出　　处：《中国科学：技术科学》2017年第9期985-991,共7页Scientia Sinica(Technologica)

摘　　要：跨音速条件下,大后掠飞翼布局翼身厚度分布影响激波/前缘涡干扰,进一步影响全机的失速特性.本文采用数值模拟方法,研究了跨音速时头部翼身厚度分布对小展弦比飞翼布局失速特性的影响规律及其对失速迎角附近激波/前缘涡干扰特性的影响.研究结果表明,减小机身头部厚度,将使机身背风侧第一道激波位置后移,激波/前缘涡干扰减弱,涡破裂点位置后移.将座舱位置后移10%机身长度,可使背风侧第一道激波位置后移到后缘附近,前缘涡破裂迎角增大4°左右,使全机失速迎角和可用升力系数增大,显著改善失速特性和俯仰力矩上仰特性.同时,将机头座舱位置后移,有利于减小全机的航向静不稳定裕度,提高航向静稳定性.该研究为大后掠飞翼布局气动布局设计和流动机理分析提供基础.The wing wing-body thickness of the highly swept flying wing configuration has great influence on the shock-leading edge vortex interaction at transonic speed, which would make significant effect on the stall characteristics. The effects of the nose thickness on the stall characteristics and heading characteristic of the low aspect ratio flying wing configuration are analyzed in simulated method and the flow mechanism is also studied. The results show that to decrease the nose thickness would make the position of the first shock wave and the breakdown position move back and the shock-leading edge vortex interaction will be weakened. To make the nose move back 10%c, the first shock wave in the leeward side will move back and it can delay the vortex breakdown by an angle 4°, which makes the stall angle and available lift coefficient increase. It would significantly improve the stall characteristics and the pitching moment characteristics. To decrease the thickness in nose also can make the heading static instability margin which would improve the heading performance. This study is useful reference for the layout design and flow mechanism of the low aspect flying wing configuration.

关 键 词：飞翼布局 小展弦比 激波/前缘涡干扰 翼身厚度 数值模拟 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]