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。 Research on cavity noise and its related technology is of great significance in the research and development of modern fighter aircraft. In this paper, the numerical simulation was used to calculate the subsonic flow at subsonic ratio L / D = 6. The mechanism of sound generation and the amplitude-frequency and total sound pressure levels of sound pressure at different positions of the cavity were analyzed , The flow control measures of adding spoiler on the front edge of the cavity to restrain the noise were studied. The wind tunnel test was carried out to verify the result. The calculation and test results show that the method has good effect and simple structure, , Has a certain engineering value.