Numerical simulations of the flow field around a double-wedge shaped projectile overtaking shocks, which move in two different directions, are carried out by solving unsteady compressible Navier-Stokes equations. In order to have enough grid resolution, the unified zonal fortified solution algorithm is used. Two test cases, the pursuing overtaking and the colliding overtaking are considered and discussed. The complex structure of wave systems and the aerodynamic forces are discussed. By comparing with the results acquired with the original methods, it is shown that the developed unified zonal method can be an effective and simple tool for handling complex bodies and enhancing the accuracy of numerical simulation.

The flowfields around a separating missile in supersonic free stream are studied numerically. Several typical flowfield structures in various separation distances are obtained. Two typical flow patterns are consistent very well with that observed in experiment. When the separation distance is small, the region between two stages is filled with "dead water" flow, the bottom drag of forebody is negative, the typical "afterbody effect" phenomenon occurs. When the separation distance is large, the complex interactive waves system is observed. After centain separation distance, the normal shock wave is formed in the front of the separated flow region before afterbody, hence the afterbody effect to forebody has been cut off.

The hypersonic flows around circular cylinders mounted flat plate are simulated by Reynolds-averaged Navier-Stokes equations and modified Baldwin-Lomax turbulence model. The zonal method and Roe third-order flux difference splitting scheme are used for the computation. The correspondent topological structures of flow patterns on plate surface are then obtained by topological theory. Some brief discussions are made with emphasizing on problems needed to be further studied.