The results of the axialwake at the propeller plane showed that the calculation method is reasonable.
对桨盘处轴向伴流的计算表明,计算结果是合理的。
2
Show in the experiment these results, which presents in the paper, may be used for predicting the axially attenuation of wake for the axial compressor blade.
Influence of the wake impact effect on the flow field and its average performance in a low speed axial-flow compressor was investigated by using external acoustic excitations.