低马赫数条件下气动声场流场分裂求解方法研究

A Splitting Simulation Method for Aeroacoustic at Low Mach Conditions

在低马赫数条件下,EIF方法可以将流场控制方程和声场控制方程(Hardin方程)分开求解,对振荡圆柱声场及双涡流动结构声场进行数值求解.声场方程空间推进采用3阶迎风格式,时间离散采用双时间步法推进.通过分析不同马赫数条件下的声场声压云图、声压级谱密度分布及特征频率,说明所采用的Hardin方程能较好地描述低马赫数条件下气动声场特征,同时验证了所采用的数值格式具有较好的数值精度.

EIF method by which the viscous/acoustic control equations（Hardin equations） are split at the low Mach conditions is adopted to simulate the pulsing cylinder and co-rotating vortex aero-acoustic fields. During simulations, the 3rd up-wind spatial scheme and dual-time step method are adopted. The numerical results, including sound pressure level maps, SPL density curves and characteristic frequencies, are illustrated that the Hardin equations effectively characterize the acoustic field at low Mach and the adopted numerical schemes have a good resolution to the acoustic control equations.