J0501-2-1 はく離を有する翼面境界層のバイパス遷移に関する実験的研究(流体機械の研究開発におけるEFD/CFD(2))

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This paper deals with the experimental study on the flow field around a low-pressure turbine linear cascade. The measurements are carried out at high and low inlet free-stream intensity (0.5% and 5%) for Re=130,000,based on the blade chord and the outlet velocity. Hot-wire probe measurements are conducted over the airfoil suction surface to understand transition process and behavior of the boundary layer. The results of the present experiment show that the size of separation bubble becomes smaller and transition point shifts more upstream as the free-stream turbulence intensity increases. At low free-stream turbulence intensity condition, K'H (Kelvin-Helmholtz) instability plays an important role in the separated boundary layer transition.
一般社団法人日本機械学会の論文
2009-09-12