簡便な一厚翼計算法(続報) : 薄い翼への適用

概要

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In the first report we presented a simple surface panel method for thick wing. This method uses source distributions (Hess and Smith type) on the wing surface and discrete vortex distributions arranged on the camber surface according to Lan's quasi-continuous vortex lattice method (QCM). Since these singularities satisfy automatically the Kutta condition, we need not use any iterative procedure. We named this method SQCM (Source and QCM). SQCM gives accurate results for thick wings. But it starts to fail when the thickness-to-chord ratio is less than 0.05. In this paper we improve the calculation method of the velocity induced at the control points on the wing surface from the vortex distributions on the mean camber surface. The improved SQCM gives reasonable results for 2-, 3-D thin wings and one-bladed propellers.
社団法人日本船舶海洋工学会の論文
1996-09-04