曲面入口部をもった二次元超音速翼列の流入場について

概要

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This paper deals with an analytical study of the inlet-flow field for a two-dimensional cascade, where the axial flow is subsonic and the relative flow is supersonic. The flow model accounts for the case where the suction surface of a blade is a convexed line in the entrance region. Using the ana1ysis, the complete inlet-flow field can be constructed, the losses due to shock waves being estimated. Two numerical examples for the different circular entrance regions are given in the case where either Mach number is 1.6 at the end in the entrance region. The results in either case indicate that the pressure amplitude decreases below about 4% of the dynamic pressure at infinite distance upstream and the losses due to shock waves are neglegibly small.
一般社団法人日本機械学会の論文
1963-05-25