Adaptation of the computational grid to a moving wing-fuselage intersection via nurbs and radial basis

Abstract

This paper proposes two approaches to automatically adapt the computational grid at the presence of moving intersections between surface components, such as wing-fuselage assemblies. The first method is based on the underlying CAD definition, which is represented by Non-Uniform Rational B-Splines (NURBS). The second method employs Radial Basis Functions (RBFs). Both methods have been tested to fix the surface grid of an DLR F6 wing-body configuration, where the wing geometry has been deformed at the intersection with the fuselage. The proposed strategies are suitable for both structured and unstructured computational grids and can be deployed in an industrial context to adapt the computational grid upon deformations of surface components