A computational aeroacoustics approach is applied to studying sound propagation in subsonic and supersonic nozzle.
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。
A computational aeroacoustics approach is applied to studying sound propagation in subsonic and supersonic nozzle.
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。
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