パネル法を利用した翼列の逆問題

概要

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A design method for two-dimensional airfoils in cascades is presented. This is based on the panel method using piecewise constant vortices. Incompressible potential flow is assumed. Pressure distributions on the upper and lower surfaces are prescribed. The changes of the intensity of vorticity are calculated so as to make the difference of the pressure distributions detween prescribed and calculated equal zero, and the profile is modified in order that he changes of surface velocity induced by these vorticity variations satisfy the boundary condition. The design code gives satisfactory solution after several iterations. Three numerical results are shown. In each case the pressure distribution of Gostelow's cascade is given as specified. Initial guess profiles are (1) Gostelow's airfoil but partly flattened upper surface, (2) Gostelow's airfoil but flat lower surface, and (3) NACA 0012 airfoil. The obtained profiles agree well with Gostelow's airfoil.
一般社団法人日本機械学会の論文
1989-07-25