摘要
以类X-51A高超声速飞行器为研究对象,重构了其机体外形及内部超燃冲压发动机的一体化模型,并通过数值方法研究了该目标巡航状态下的气动与燃烧耦合流场特性。数值分析结果表明:类X-51A飞行器高压区主要集中在机体头部、进气道压缩段、进气道入口侧壁及尾翼前缘,且内部燃烧室的总体压力显著高于机体表面的;燃烧室内靠近两侧壁面的喷孔燃料喷注深度高于中间喷孔的,下游喷孔喷注深度高于上游喷孔的,凹腔附近喷孔喷注深度高于无稳焰结构的壁面喷孔的;燃烧产物羽流长度超过50m,且持续向机体上方发生偏移。计算结果可为类X-51A及相关飞行器红外探测与目标识别等技术提供流场数据参考。
The X-51A type hypersonic vehicle was taken as the research object,an integrated model of the body shape and internal scramjet was reconstructed.The aerodynamic and combustion coupled flow field characteristics of the X-51A type hypersonic vehicle under cruise state were studied using numerical methods.The results of numerical analysis show that the high pressure regions of the X-51A type hypersonic vehicle are mainly concentrated in the body head,the inlet compression section,the inlet sidewall,the leading edge of the tail wing,the overall pressure of the internal combustion chamber is significantly higher than that of the body surface;the injection depth of fuel nozzle near the two sides of the wall in the combustion chamber is higher than that of the middle fuel nozzle,the injection depth of the downstream fuel nozzle is higher than that of the upstream fuel nozzle,the injection depth of the fuel nozzle near the cavity is higher than that of the fuel nozzle on the wall without flame stability structure;the length of the combustion product wake exceeds 50 m,it continues to shift to the upper part of the aircraft.The calculation can provide flow field data reference for technologies such as infrared detection and target recognition of X-51A and related aircraft.
作者
董天洋
林志勇
孟夏莹
王彪
秦顺
DONG Tianyang;LIN Zhiyong;MENG Xiaying;WANG Biao;QIN Shun(School of Aeronautics and Astronautics,Sun Yat-sen University,Shenzhen 518107,Guangdong,China;National Key Laboratory of Scattering and Radiation,Shanghai 200438,China)
出处
《制导与引信》
2024年第1期7-12,共6页
Guidance & Fuze
基金
上海航天科技创新基金(SAST2021-003)。
关键词
高超声速
超燃冲压发动机
气动特性
喷注特性
数值仿真
hypersonic
scramjet
aerodynamic characteristics
injection characteristics
numerical simulation
