A hybrid computational aeroacoustic method with permeable boundary is developed to evaluate non-compact noise induced by low Mach number flow over arbitrarily shaped bodies. Based on Lighthill’s equation and the boundary element method, the unified integral equations are established in which the integral boundary surrounding the objects can be selected arbitrarily. Validation studies are developed for noise induced by two-dimensional NACA0012 airfoil and three-dimensional circular cylinder. For NACA0012 airfoil, the directivity patterns of calculated noise with different permeable boundaries agree well with Howe’s analytical solution for trailing edge model. The acoustic noise generated by circular cylinder has a good agreement with Revell’s experimental data and FW-H equation. It demonstrates that the noise predicted by different permeable boundary is as accurate as that calculated by the body surface.

开发了一种具有可渗透边界的混合计算空气声方法，以评估由低马赫数流过任意形状的物体引起的非紧凑噪声。基于Lighthill方程和边界元法，建立了统一的积分方程，可以任意选择物体周围的积分边界。针对二维NACA0012机翼和三维圆柱体引起的噪声进行了验证研究。对于NACA0012机翼，计算得出的具有不同渗透边界的噪声的方向性模式与Howe的后缘模型解析解决方案非常吻合。圆柱体产生的声噪声与Revell的实验数据和FW-H方程具有良好的一致性。