超音速多圆弧(MCA)叶型叶珊的研究

本文提出了含脱体激波的叶栅有旋超音速流场的特征线起始线计算方法。采用激波嵌入法解完全的欧拉方程,计算了含脱体激波的多圆弧叶栅的超音速进口流场。本文发展了一种将超音速流场计算与亚音速扩散损失计算的尾迹法相关联的计算超音速叶栅损失的方法,可分别确定激波损失和亚音速扩散损失。 

INVESTIGATION OF SUPERSONIC MULTIPLE CIRCULAR ARC (MCA) AIRFOIL CASCADE OF AXIAL-FLOW COMPRESSOR

A computational method of characteristics initial-value line in the rotational supersonic cascade flow field with detached shock waves is presented. With the solution of complete Euler flow equations by shock fitting method, a MCA cascadesupersonic inlet flow field containing detached waves is computed. The calculateddetached shock waves before the cascade and the pressure distribution in the supersonic region are satisfactory. From the calculated results of the flow field, the relation between the Mach number and the unique incidence, which meets the design requirements can also be obtained.In our investigation ,the loss-computational method of the supersonic cascade is also firstly presented, which correlates the computation of supersonic flow field with the wake method of subsonic profile. This method can determine the shock loss and the subsonic profile loss separately. Agreement between the calculatedand the measured total loss is quite good.