航空機の空気力学的問題への有限要素法の応用(第1報)

抄録

In the present paper, the finite element method is applied to the calculation of steady incompressible potential flow around a three-dimensional lifting body like an aircraft. The MORINO's formulation is modified in such a way that the lift acting not only on the wing, but also on the body is taken into account for a wing-body configuration. The problem is formulated in a form of an integral equation for the disturbance velocity potential on the body surface. By the use of the finite element method combined with the collocation method, this integral equation is reduced to a set of linear algebraic equations.
The present method has been applied to obtaining the pressure distribution acting on the following three-dimensional lifting bodies: a tapered wing, ⊥-wing, _??_-wing, a cross wing with or without a fillet, and a wing-body configuration. The results obtained by the present method have been found to be in good agreements with those obtained by wind tunnel experiments. It has been also found that the aerodynamic interference effect can be well predicted by the use of the present method.