摘要
空腔噪声及其相关技术的研究在现代战机研发中具有重要意义。本文采用数值模拟的方法计算了长深比L/D=6的空腔在亚音速下的流动,分析了其发声的机理,以及空腔不同位置处声压的幅频和总声压级特性,研究了在腔体前缘加装扰流板以抑制噪声的流动控制措施,并在此基础上进行了风洞试验验证,计算及试验结果表明:该方法效果良好,且结构简单、实施方便,具有一定的工程实用价值。
The investigation of cavity acoustics and related technologies are very important in the development of advanced fighters.A numerical study of a cavity with length-to-depth ration of 6 is conducted to analyse the acoustic mechanism,sound pressure frequency spectrum and the overall sound pressure levels.The effect of using the leading edge spoiler is studied by both numerical simulation and wind tunnel test to suppress the acoustic noise.The results indicate that leading edge spoiler can obviously improve the cavity＇s acoustic environment.Considering the very simple structure and favorable effect,the control method has some practical value in engineering.
出处
《航空工程进展》
2011年第3期245-248,266,共5页
Advances in Aeronautical Science and Engineering
关键词
空腔噪声
扰流板
流动抑制
cavity acoustics
spoiler
flow control
