矢量喷流对细长体大迎角非对称流动影响研究  

EFFECT OF VECTORING JET ON ASYMMETRICAL VORTEX OF SLENDER BODY

作　　者：王延奎[1] 张永升[1] 邓学蓥[1] 杨水锋[1] 于晓伟[1] 

机构地区：[1]北京航空航天大学流体力学教育部重点实验室,北京100083

出　　处：《力学学报》2007年第3期289-296,共8页Chinese Journal of Theoretical and Applied Mechanics

基　　金：国家自然科学基金重点项目(10432020);国防预研基金项目(51413020104HK0101);国防预研基金重点项目(9140A13020106HK0111)资助

摘　　要：采用测压方法研究了矢量喷流对细长旋成体大迎角非对称流动的影响特性．实验结果表明:矢量喷流对细长旋成体大迎角非对称侧向力有明显的抑制作用,该抑制作用是通过喷流诱导作用,改变其空间绕流涡系结构的分布来实现的,但是矢量喷流的存在并不能改变大迎角机身空间绕流涡系的本质结构;随着迎角的增大,矢量喷流对细长旋成体大迎角非对称流动的影响区域不断前移,甚至影响到头部;随着喷流落压比的增加,矢量喷流对细长旋成体大迎角非对称侧向力的抑制作用加强,但当喷流落压比达到临界落压比后(即喷管出口处达到设计马赫数时),喷流影响作用将不会随喷流落压比的增加而改变．This paper studies the effect of vectoring jet on the transverse aerodynamic characteristics of a slender body. The results show that： 1） the side force of the slender body caused by asymmetric vortices at a high attack angle can be reduced by vectoring jet effectively. 2） with the increase of the attack angle, the affected zone of vectoring jet is expanded and reaches the nose of the slender body. 3） with the increase of the pressure of the vectoring jet, the effect of jet on the side force of the slender body is increased. The Mach number of the nozzle is the key simulation criterion for the thrust vectoring test. The test was carried out in D4 wind tunnel in Beijing University of Aeronautics and Astronautics.

关 键 词：大迎角 细长旋成体 矢量喷流 非对称流动 风洞实验 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]