超声速多喷流干扰流场特性研究  

STUDY ON THE CHARACTERISTICS OF INTERACTION FLOWFIELDS INDUCED BY SUPERSONIC MULTI-JETS

作　　者：王军旗[1,2] 李素循[1] 

机构地区：[1]中国航天空气动力技术研究院北京100074 [2]山东大学能源与动力工程学院,济南250061

出　　处：《力学学报》2009年第4期575-583,共9页Chinese Journal of Theoretical and Applied Mechanics

基　　金：国家自然科学基金重大项目资助(90205028);supported by the Major Program of the National Natural Science Foundation of China(90205028)

摘　　要：研究了旋成体上超声速来流与超声速横向多喷流相撞产生的层流干扰流场特性.数值方法针对三维可压缩Navier-Stokes方程按二阶精度Roe格式进行离散,采用基于多区对接网格技术的有限体积法.数值模拟结果描述了多喷流干扰流场的空间结构以及激波/边界层干扰引起的分离范围,探讨了沿流向等间距排列的喷口个数对表面和空间流场结构以及压力分布的影响规律.结果表明,第一喷口对多喷流干扰流场主要结构和喷口上游表面分离范围起主导作用.其中三喷流流场数值模拟的对称面激波结构与实验纹影结果进行对比,符合较好.Transverse jet technology has been applied to many aircrafts as an effective way of attitude control. It can provide thrust more rapidly and is affected by less flight conditions than conventional aerodynamic surface control. Therefore, the maneuverability of the aircraft is enhanced. And less aerodynamic surfaces are needed, thereby the weight is reduced and the stealth performance is improved. Recently, the method of jet attitude control is paid more and more attentions. When a sonic or supersonic jet is injected laterally into supersonic or hypersonic free stream, the complex jet interactive flowfields is generated which involves complex flow structures such as shock/boundary layer in- teraction, multi-shocks interaction, flow separation vortices, and flow reattachment, etc. Although considerable investigations have been carried out for nearly half a century, but there are many issues unresolved until now in understanding the flowfields characteristics and flowing mechanism. The characteristics of the interaction flowfields induced by lateral supersonic single/multi jets mounted longitudinally on the revolution body had been studied by numerical simulation in this paper. The three dimensional compressible laminar N-S equations were solved by finite volume method with Roe＇s two-order spatial scheme and multi-block structure grid. The method was validated qualitatively and quantitatively by experimental schlieren photo about the shockwaves showed in three jets interaction flowfields. The spatial structures of single/multi jets interaction flowflelds and separation regions induced by shockwave/boundary layer interaction were described in this paper. Four cases including single jet, twin jets, triple jets and five jets interaction flowfields had been simulated numerically and analyzed. It is shown that the influences of the first jet on the Structure and separation region of interaction flowfields upstream of the jets was dominant.

关 键 词：横向喷流 多喷流 超声速流 激波/边界层干扰 

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]