簡便なパネル法による非定常3次元翼問題の解法

概要

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A simple surface panel method (SQCM) has been successfully applied to steady state problems and unsteady two-dimensional wing problems. SQCM 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). In this paper, we extend SQCM to the unsteady problems for three-dimensional wing by combining the source panels and unsteady QCM which has been successfully developed. We consider the unsteady Kutta condition that the pressures must coincide with each other on the upper and lower surfaces at the trailing edge. In the steady problem, SQCM satisfies the Kutta condition by setting zero normal velocity on the camber surface at the trailing edge. But it is not usually equal to zero in the unsteady problem but a finite normal velocity exists. In the unsteady two-dimensional wing problem, we obtained this normal velocity by iteration for the equal pressure condition at the trailing edge. So, we extend this Kutta condition to unsteady three-dimensional wing and show that SQCM gives reasonable results for unsteady three-dimensional wing problems (Wagner problem, sinusoidal gust, heaving oscillation and pitching oscillation problems).
社団法人日本船舶海洋工学会の論文
1997-09-04