簡便なパネル法による翼型逆問題の一解法

概要

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We apply a simple surface panel method to design wings corresponding to given pressure distributions. This method uses source distributions (Hess and Smith type) on the wing surface and discrete vortex distributions arranged on the camber plane of the wing according to Lan's quasi-continuous vortex lattice method (QCM). Then these singularities are determined at a time by solving simultaneously the boundary conditions that the normal velocity should be zero on both the wing surface and the camber plane of the wing. Since these singularities satisfy automatically the Kutta condition, we need not use any iterative procedure. We named this method SQCM (Source and QCM). In this paper we show the numerical procedure to obtain wings which have given pressure distributions. Several two-dimensional numerical results are shown. In each case wings are successfully obtained corresponding to given pressure distributions. It is also found that the present method does not depend on initial wing geometry and the convergence is fast.
社団法人日本船舶海洋工学会の論文
1998-03-29