簡便なパネル法による非定常2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, for example, hydrofoils, marine propellers, etc. 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 two-dimensional wing problems 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. SQCM's steady state Kutta condition is zero normal velocity on the camber surface at the trailing edge. But it is not always equal to zero in the unsteady problem and a finite normal velocity exists. We obtain this normal velocity to satisfy the equal pressure condition at the trailing edge and show that SQCM gives reasonable results for unsteady two-dimensional wing problems (Wagner problem, heaving oscillation, sinusoidal gust and pithcing oscillation problems).
社団法人日本船舶海洋工学会の論文
1997-03-29