带舵旋成体侧向喷流流场特性分析  

Analysis on flow field characteristics of lateral jet on slender body

作　　者：赵法明 王江峰[1] 

机构地区：[1]南京航空航天大学航空宇航学院,南京210016

出　　处：《航空动力学报》2016年第3期726-732,共7页Journal of Aerospace Power

基　　金：江苏高校优势学科建设工程项目

摘　　要：针对带舵旋成体外形,来流马赫数为2.0,迎角为0°,10°和20°,喷口位于×字舵中间,首先开展了喷主流干扰流场的数值模拟与风洞实验校验,得到相符的喷口附近子午线压力分布,验证了数值模拟方法的可行性;然后根据数值模拟得到的喷主流干扰流场结构和流动参数分布,分析了喷主流干扰流场结构随迎角的变化特点;最后从喷口附近旋成体和尾舵表面压力分布的变化分析了喷主流干扰对气动力/力矩放大因子的影响.研究结果表明:随迎角增大,喷流前激波向喷口靠近,分离区减小,喷主流压比增大,喷流穿透高度增大;气动力/力矩放大因子均大于1.0,随迎角增大,放大因子减小.喷口位于×字舵中间时,喷主流干扰对喷流直接力有增益作用;×字舵的存在减弱了喷流的包裹作用,对流场起到了有利干扰.Study was carried out for a slender body with rudders,with free stream Mach number of 2.0,attack angle of 0,10,20 degrees respectively,and the jet spout located between the×-shape rudders.First of all,numerical simulation and wind tunnel tests were carried out,and consistent radial pressure distribution near jet spout was obtained,verifying the feasibility of numerical simulation method.And then,the characteristics of change with attack angle of the interaction flow field were analyzed on the basis of flow field structure and flow parameters distribution obtained from numerical simulation.At last,influence of jet interaction on amplification factors was examined according to surface pressure distribution of slender body and rudders near jet spout.Results showed that,with increasing angle of attack,shock before jet moved towards jet spout with reduction of separation region,and pressure ratio increased with augmentation of penetration height.Amplification factors were larger than 1.0and decreased with increasing angle of attack.When jet spout was located between ×-shape rudders,jet interaction was beneficial to the enhancement of jet force.Existence of×-shape rudders eased the wraparound effect of jet,leading to favorable interference to the flow field.

关 键 词：流场特性 超声速主流 侧向喷流 风洞实验 放大因子 

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]