翼の後縁近傍乱流境界層の乱流構造

概要

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An experimental investigation of a turbulent boundary layer in the vicinity of the trailing edge of an airfoil is reported in this paper. The airfoil (NACA65-010) is located in a wind tunnel at an angle of attack of 0° and 8°. The mean-velocity, turbulent energy, Reynolds stress,auto-correlation function and energy spectrum are measured. Further, the structure of the outer intermittent region is investigated using conditional sampling. The main results are summarized as follows: The turbulent energy at the pressure side increase compared with the suction side, but a reversed characteristic is observed for Reynolds stress. The center of intermittency moves wallward and the width of the intermittent zone increases at the pressure side. The turbulence structure of the turbulent boundary layer at the pressure side is different from that of a fully developed turbulent boundary layer.
一般社団法人日本機械学会の論文
1987-12-25