超音速空腔噪声非线性数值模拟及影响因素研究

摘要

将雷诺平均Navier Stokes(RANS)方程与非线性噪声求解(NLAS)方法相结合,对超音速空腔噪声开展研究.首先与Ma=2状态下武器内埋及分离(WICS)风洞试验进行了对比验证,各监测点的声压级计算值和试验值吻合较好,表明基于湍流重构的NLAS方法能较好地模拟超音速空腔类噪声问题且能显著减少计算网格.对大曲率前缘超音速空腔流动噪声展开了分析,在Ma=2.5时,空腔最大声压级达到了162 dB,会造成结构损伤,必须采取相应的降噪措施.在此基础上分别研究了飞行马赫数、高度、攻角、侧滑角变化对声压频谱特性与总声压级的影响,为超音速飞行器的空腔结构设计提供一定的工程参考价值.%The Non-Linear Acoustic Solver(NLAS) is employed to study the cavity noise in supersonic combined with Reynoldsaveraged 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 indicate that the NLAS method which is based on turbulence reconstruction could well simulate the cavity noise in supersonic and reduce mesh numbers.The cavity noise with large curvature edge is researched.The maximum sound pressure level is 162dB when the Mach number is 2.5,and so the corresponding noise reduction measure should be adopted,otherwise the structure damage will occur.On this basis,the effects of the flight Mach number,altitude,angle of attack,sideslip angle on the acoustic pressure frequency spectrum and overall pressure level are analyzed to provide some engineering references for the cavity design in supersonic.