超音速非定常流数値解析用パネル法プログラムの定式化

概要

論文の詳細を見る
For the design of aeronautical vehicles, it is necessary to predict not only steady aerodynamic characteristics but also unsteady ones. However, current numerical tools for the latter are insufficient especially in the case of supersonic flow. In this paper, mathematical formulation of a boundary-element-type panel method is achieved for supersonic unsteady flow calculations. Linearized Euler equation is transformed to an integral form, which is partially simplified according to Morino's method. The integral equation is discretized to a linear algebraic equation by raplacing the boundary surface with an assembly of triangular panels. To ensure the continuity of doublet density on panel edges, linearly varying distribution is adopted on each panel. The shape of the panel assembly and its attitude can be specified arbitrarily within the limit of linearization validness, which enlarges the ability of this method compared to the current panel method programs for supersonic unsteady flow.
岡山理科大学の論文