级间分离反向喷流风洞试验和数值模拟研究  

Wind tunnel experimental and numerical simulation of interstage separated reverse jet

作　　者：叶瑞 赵弘睿 陈农[1] 杨云军[1] YE Rui;ZHAO Hongrui;CHEN Nong;YANG Yunjun(China Academy of Aerospace Aerodynamics,Beijing 100074,China)

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《兵器装备工程学报》2023年第S01期277-283,共7页Journal of Ordnance Equipment Engineering

摘　　要：在FD-16风洞中开展Ma=6级间分离反向喷流风洞试验,采用数值模拟对不同间距、不同夹角和有无喷流状态下的气动干扰特性进行了分析研究,结果表明:后体两侧喷流与来流相互作用产生的干扰,使得前体法向力减小,俯仰力矩增大;后体的法向力和轴向力增大。在20~140 mm前后体间距范围内,喷流引起的弓形激波与前后体间隙之间的相互作用主导了流动变化。在-4°~4°夹角范围内,夹角变化对前体和后体的气动干扰影响较小。喷流与来流相互作用产生的干扰对前体气动特性的影响远大于后体。This paper carries out an interstage separated reverse jet experiment under a Mach 6 condition in the wind tunnel FD-16,in which aerodynamic interference characteristics are investigated through numerical simulation,including different spacing,different angles and different environments with or without jet.The results show that the interference caused by the interaction of the reverse jet flows reduces the normal force of the forebody and increases the pitching moment,and increases both the normal force and axial force of the afterbody.Within a spacing range from 20 mm to 140 mm,the interaction between the bow shock waves caused by the jet and the gap between the front and the rear bodies dominate the flow change.The change of the angle in the range from-4°to 4°has little impact on the aerodynamic disturbance of the forebody and the afterbody.The influence of the interaction between the jet and the incoming flow on the aerodynamic characteristics of the forebody is much greater than that of the afterbody.

关 键 词：面对称外形 级间分离 喷流干扰 风洞试验 数值模拟 气动特性 

分 类 号：V211.24[航空宇航科学与技术—航空宇航推进理论与工程]