Computer-aided method for a cost-optimized calculation of variable distributions over an aerodynamic surface

A computer-aided method suitable for assisting in the design or analysis of an aircraft by providing a variable distribution V over the surface of an aircraft or an aircraft component inside a predefined parameter space by means of a reconstruction of the results obtained through computations for an initial group of points in the parameter space using a CFD model in connection with a structured mesh defined on said surface, characterized in that in each of said computations it comprises the following steps:

• a) Selecting relevant shock wave structures along mesh lines in the chord direction taking place between a first point and a last point in the mesh line, being defined by its thickness δsw, its position ssw in the mid point between said first point and said last point and the variable jump ΔV between the last and the first point;
• b) Decomposing said variable distribution V into a smooth variable distribution Vsmooth and a shock wave variable distribution Vjump corresponding to said relevant shock wave structures;
• c) Obtaining the variable distribution V at any point of the parameter space as a reconstruction of the smooth variable distribution Vsmooth and the shock wave variable distribution Vjump obtained for said point from the values obtained in step b).