与えられた圧力分布を持つ翼型の計算法

概要

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In this paper, a method of calculating airfoil section form with given pressure distribution is treated considering the effect of viscosity. The velocity on the airfoil surface and the magnitude of circulation around airfoil differ between perfect and viscous fluids and these differences arise from the formation of boundary layer on the airfoil surface. In this method, the boundary layer thickness is calculated theoretically at first, then the above-mentioned differences are estimated assuming the thin layer covering airfoil with height of displacement thickness of the boundary layer is filled with streaming fluid issued from the imaginary source distribution on the airfoil surface, and hence corresponding pressure distribution of the perfect fluid is obtained. Then airfoil form is calculated for this corrected pressure distribution by the method already obtained by the senior author in the case of perfect fluid. Both cases of isolated airfoil and wing lattice are treated. An example of isolated airfoil (N.A.C.A. 4412,α=12°, R=3・10^6) is shown in the original paper.
一般社団法人日本機械学会の論文