推力转向喷流与高速主流干扰参数影响规律的数值模拟研究  

The study of the parameters' infection between vectoring jet and high speed main flows interaction

作　　者：司芳芳[1] 袁先旭[1] 李建强[1] 陈琦[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《空气动力学学报》2012年第5期583-591,共9页Acta Aerodynamica Sinica

摘　　要：针对一种简化的飞机模型,数值模拟了推力矢量尾喷流与高速主流的干扰效应,系统总结了来流马赫数、攻角、喷管偏转角、喷流马赫数、喷流总压、喷流总温等参数对飞机气动特性的影响规律,分析了流动机理,结果表明:对于该简化战斗机模型,推力矢量尾喷流对高速主流的干扰局限于尾部局部区域,对全机气动特性的影响较小,仅在较大攻角下才有一定体现;但高速主流对尾喷流的干扰显著,推力矢量角损失随来流马赫数和攻角的增大而增大。The thrust vectoring control technology The computational study of interaction flows between is the main technology for the 4th generation fighter vectoring jet and high speed main flow around a simpli fled fighter configuration is presented. The infections of the parameters such as Mach number of main flow, attack angle, nozzle deflection angle, Mach number, total pressure and total temperature of jet flow are sys- tem researched. The physical mechanism of the main flow/vectoring jet flow interaction is also analyzed. Nu- merical simulation results show that for the simplified fighter configuration, the thrust vectoring jet effect on the high speed main flow is only effects on the aircraft components near the nozzle exit and have little effect on the aerodynamic characteristics of aircraft except at high angles of attack. However, the high speed main flow has strong interaction with thrust vectoring jet flow. With the increasing of the angle of attack and Mach number the decrease of thrust vectoring angle are increasing.

关 键 词：推力矢量控制技术 数值模拟 马赫数 攻角 喷流 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]