A domain decomposition method based on chimera grids is proposed for Euler solver. The solver is developed based on a class of second order TVD difference schemes with a new entropy condition. The developed procedure is capable of handling the steady and unsteady flows over multibodies located separately, or in contact, or under relative motion with each other. The procedure is demonstrated by a test case of supersonic flows over two circular cylinders parted by different distances. A detail result is presented. The procedure is then applied to simulate the rotating flow fields over rockets with canard rudders.

A grid generation technique adaptable for flows with complex geometrical characteristics is developed. The procedure is developed in such a way that the surface grids are first constructed and/or reconstructed in multi-block manner according to the data given at typical section of the body, utilizing the nonuniformed rational B spline (NURBS) surface representation commonly employed in CAD technique. The blocks consisting of the flow field are decomposed in accordance with the geometrical and flow characteristics of the specified problem, and the boundaries of the blocks can thus be constructed accordingly. Based on the surface grids generated, a multi-block grid system for the entire flow field can then be built up by using numerical, algebraic or mixed methods. As an illustration, the grids generated by the developed technique for several space transport systems are presented.