摘要
采用计算气动声学方法研究了管道近音速区的声传播和声波与激波的相互作用问题。空间离散采用高阶DRP格式,时间离散采用低耗散低频散的龙格库塔方法,边界条件采用Giles的特征变量一维非定常无反射边界条件。计算结果和解析解的精确吻合表明,计算中应用的这种高阶的DRP格式有很高的分辨率和很好的稳定性,适合声传播的计算。
A computational aeroacoustics approach is applied to study sound propagation in subsonic and supersonic nozzle. The spatial derivatives are discretized by DRP scheme, and the low dissipation and dispersion Runge-Kutta scheme is used for time integration. The Giles' characteristic ID unsteady non-reflecting boundary conditions are applied to the inflow and outflow boundary regions. Numerical results agree well with analytical solutions and it reveals that the DRP scheme performs very well because of the high resolution and robust stability and is capable of calculating sound propagation.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2003年第1期15-19,共5页
Journal of Aerospace Power
基金
国家自然科学基金资助项目(10072009)
