摘要
高马赫数(Ma>2)武器舱剪切层更强、更稳定,其噪声产生机制与通常的亚、跨、超声速武器舱流动不同,导致用来抑制空腔噪声的流动控制措施也不同。分别采用数值模拟和风洞试验2种手段,研究了圆柱形机身和马赫数对空腔流动特性的影响,以及前缘锯齿、前缘立柱、前缘横柱、前缘挡板等不同被动流动控制措施对高马赫数武器舱声压级特性的影响,为高马赫数武器舱的流动控制措施设计和研究提供参考。研究表明:圆柱形机身对空腔底部的压力分布会产生影响,压力分布的不均匀性增大,后壁附近的压力峰值增大;对通常的亚、跨、超声速武器舱流动较为有效的被动流动控制措施,对高马赫数空腔流动效果不明显,甚至会加大武器舱内的噪声等级,需要开展更为深入的研究,以设计更为有效的流动控制措施。
The noise generation mechanism of weapon bays at a high Mach number(Ma>2)is different from that of the subsonic,transonic,and supersonic weapon bay flow because of the stronger and more stable shear layer.This discrepancy may also lead to different flow control measures for cavity noise suppression.Using numerical simulations and wind tunnel tests,this study examines the effects of the cylindrical fuselage and Mach number on cavity flow characteristics,and of different passive flow control measures such as leading edge serrations,leading edge columns,leading edge transverse columns and leading edge baffles on the sound pressure level of a weapon bay at a high Mach number.This study provides a reference for the design and research of flow control measures for a high Mach number weapon bay.The results show that the cylindrical fuselage has an impact on the pressure distribution at the cavity bottom,that the unevenness of the pressure distribution increases,and that the pressure peak near the rear wall increases.The passive flow control measures,which are more effective for the subsonic,transonic and supersonic weapon bay flow,are not effective for the high Mach number cavity flow,and even increase the noise level in the weapon bay.Further research is needed to design more effective flow control measures.
作者
张培红
陈洪杨
张杰
罗磊
周方奇
贾洪印
ZHANG Peihong;CHEN Hongyang;ZHANG Jie;LUO Lei;ZHOU Fangqi;JIA Hongyin(Computational Aerodynamic Institute of China Aerodynamics Research and Development Center,Mianyang 621000,China;High Speed Aerodynamic Institute of China Aerodynamics Research and Development Center,Mianyang 621002,China)
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2023年第11期2913-2920,共8页
Journal of Beijing University of Aeronautics and Astronautics
基金
国家数值风洞工程项目。
关键词
武器舱
数值模拟
风洞试验
流动控制
声压级
weapon bay
numerical simulation
wind tunnel test
flow control
sound pressure level
