跨、超声速X形鸭翼-弹身组合体旋涡运动  

Vertex Development on a Cruciform Canard-Body Configuration at Tran-Supersonic Speeds

作　　者：洪金森[1] 

机构地区：[1]北京空气动力研究所,北京100074

出　　处：《空气动力学学报》2000年第z1期32-37,共6页Acta Aerodynamica Sinica

摘　　要：应用蒸汽屏方法显示跨、超声速Ｘ形鸭翼－弹身组合体旋涡运动。实验马赫数 ０．９０～４．０１，攻角范 ５°～３２°。截面图象表明随马赫数增大，涡进尺度减小。在低马赫数 小攻角下，截面流场中旋涡结构呈现对流和扩散效应，旋涡间相互诱导生成流面；在中等 攻角下，弹身上方出现四个鸭翼涡，在横流平面上形成“蛙跃”趋势；在大攻角下，流场 由弹身不对称涡主导，鸭翼涡被体涡缠绕、合并。在高马赫数下，截面流场上，翼涡紧缩 成“点涡”状。体涡两侧产生横流激波。Vortex development over a cruciform canard-body configuration were visualized by using vapor-screen technique at tran-supersonic speeds. The experiments were carried out for Mach numbers 0.90-4.01 in angles-of-attack range 5°~32°. The crossflow section shows that the vortex wake scales decreases with increasing Mach number. At small Mach number and lower angles-of attack, the fin vortex of a crossflow section presents the effects of convection and diffusion. The interaction of vortices generate the free streamsurface. At intermediate angles-of attack, the four fin vortices displayed over body tend to 'leapfrog'. As angles of ruck increases higher further, they are wound and merged by asymmetric body vortices which dominate the flowfield. In the range of large Mach number, the tightly coiled character of the fin vortices becomes eventually 'point vortices' and there is a crossflow shock wave on each side of the pair of symmetric body vortex.

关 键 词：流动显示 旋涡运动 鸭翼-弹身外形 高速风洞试验 

分 类 号：V221.41[航空宇航科学与技术—飞行器设计] V211.74