Patent ID: 8676544
Filing Date: 2014-03-18
Classification: B64F,G06F

Abstract:
1. A method for predicting the aerodynamic performance of an aircraft element under predetermined conditions, the method performed by a computer including a processor, the aircraft element having, under the predetermined conditions studied, at least one break at least partially separating two parts of the aircraft element that cannot be modeled with a common envelope form or that it is not desirable to model with a common envelope form, the method comprising: creating, by the processor, a digital object representative of a form that the aircraft element assumes under the predetermined conditions studied, and the digital object is created so that each break is represented therein; creating, using the processor, a meshing around the digital object; on the basis of the predetermined conditions studied, carrying out digital aerodynamic simulation computations using the meshing; for each break, creating a totally non-coincident boundary plane at the joining between the two parts delimited by the break, at the level of the break; making the meshing, for each totally non-coincident boundary plane created, by generating a partial structured meshing around each of the two parts delimited by the created totally non-coincident boundary plane, the two partial structured meshing not overlapping each other and being independent of one another; and carrying out the digital aerodynamic simulation computations, by using an aerodynamic computation code processing a totally non-coincident join, wherein the created totally non-coincident boundary plane designates a plane on respective sides of which the two partial structured meshing are made, the two partial structured meshing being generated such that points of one meshing located on the created totally non-coincident boundary plane are not ensured to coincide with points of the other meshing located on the created totally non-coincident boundary plane.