Prediction of aerodynamic noise is the key technology for the internal weapon bay of supersonic aircraft. Nonlinear numerical simulation is proposed as a new method to analyze noise recently. The Non-Linear Acoustic Solver (NLAS) is employed to study the cavity noise in supersonic combined with Reynolds-averaged Navier-Stokes (RANS) equation. It is shown by the comparison between the calculated results and the WICS wind tunnel tests when the Mach number is 2, the sound pressure level of every monitoring point is in good agreement with experiments. It indicates that the NLAS method which is based on turbulence reconstruction could well simulate the cavity noise in supersonic and reduce mesh numbers. Based on this, the contribution to aerodynamic noise suppression made by active control measure such as adding jet screen at the leading edge of cavity is investigated. It is found that jet screen improves flow condition and increases cavity safety, therefore, it is suitable for suppression of aerodynamic noise under supersonic condition.

空气动力噪声的预测是超音速飞机内部武器舱的关键技术。非线性数值模拟是近来提出的一种分析噪声的新方法。非线性声学求解器（NLAS）用于结合雷诺平均Navier-Stokes（RANS）方程来研究超音速中的腔噪声。通过计算结果与马赫数为2时WICS风洞试验的比较可以看出，每个监测点的声压级与实验吻合良好。这表明基于湍流重构的NLAS方法可以很好地模拟超音速腔噪声，并减少网格数。基于此，研究了通过主动控制措施（例如在腔体的前缘增加射流滤网）对空气动力学噪声抑制的贡献。发现射流筛网改善了流动条件并增加了腔体的安全性，因此，它适合于在超音速条件下抑制空气动力噪声。