An automatic scheme for the simulation of the e ow about a deforming aircraft cone guration is presented. The scheme utilizes the overset grid method to perform elastic deformations and to vary the elevator dee ection angle, thus avoiding the regeneration of the computational mesh. As a part of the scheme, a new method for automatic collar grid generation is developed and presented. The method is especially efe cient for sharp intersections. The generated collar grids are smooth and orthogonal and clustered toward the walls of the intersecting geometries. The algorithm is incorporated in a e ow solver that utilizes the overset grid approach. An example is given for the case of the e ow about a maneuvering, elastic, fuselage-wing-tail cone guration. The changes to the cone guration in the course of the computation require a nonfailing automatic grid-generation procedure because of the changes to the fuselage-wing and the fuselage-tail intersection regions. The results show good agreement with computational results obtained using the patched approach.