航空学报2025，Vol.46Issue(8)：177-194,18.DOI:10.7527/S1000-6893.2024.31086
宽域高超声速飞行器可调矢量喷管方案设计与性能研究
Scheme design and performance study of adjustable vector nozzle for wide-range hypersonic aircraft
摘要
Abstract
In response to the urgent requirements for wide-range high performance,geometric adaptability of the exit,and efficient thrust vectoring capability of axisymmetric nozzles for wide-range high-speed aircraft,an adjustable vector nozzle and an internal-middle-outer three-ring adjustment scheme were designed.Numerical simulations were con-ducted on the nozzle under typical operating conditions,and the flow field structure and performance of the nozzle un-der different modes were analyzed.The results show that by adjusting the positions of the middle and outer rings through translational motion,the nozzle can adjust the exit area and has the thrust vectoring capability.In the non-thrust vectoring mode,due to the adjustable exit area of the nozzle,the overexpansion phenomenon at low nozzle pressure ratio is effectively alleviated,and the thrust performance is significantly improved.Compared with the fixed geometry nozzle,the thrust coefficient can be increased by up to 32.75%.In the thrust vectoring mode,the maximum vector angle larger than 10° can be generated at Mach number 7,while the thrust coefficient is still greater than 0.92.To fur-ther reduce the base drag of the nozzle at low Mach number,a flow control method for secondary flow intake was pro-posed,which can reduce the base drag by up to 78.5%by reducing the internal and external pressure difference of the secondary flowpath.Finally,a wind tunnel scale-down experiment was conducted.The experiment results were in good agreement with the numerical simulation results,verifying the effectiveness of the proposed design scheme.关键词
宽域高速/高超声速/可调喷管/推力矢量/底阻/风洞试验Key words
wide-range high-speed/hypersonic/adjustable nozzle/thrust vector/base drag/wind tunnel test分类
航空航天引用本文复制引用
魏礼响,徐惊雷,陈匡世,黄帅,葛建辉,宋光韬..宽域高超声速飞行器可调矢量喷管方案设计与性能研究[J].航空学报,2025,46(8):177-194,18.基金项目
国家自然科学基金(12332018) （12332018）
