翼列翼の曲げ振動による空力減衰力に関する実験的研究

概要

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Unsteady aerodynamic damping force and its chordwise distribution over a cascade blade in a bending motion were experimentally studied for the wide range of non-dimensional frequency k and inter-blade phase angle σ by use of a wind-tunnel and by the forced oscillation method. For the range of k≦1, the experimentally obtained aerodynamic damping forces agreed well with the one predicted by the subsonic unsteady potential flow cascade theory. But, in the range of 1<k≦4.2, the experimental values were less than the theoretical ones, and even negative, especially for σ <0. The reason of this discrepancy is considered to be attributed to the superposing effect of the downwash contributions from adjacent blades and the so-called boundary-layer time lag.
一般社団法人日本機械学会の論文
1984-01-28